Airworthiness Directives; Airbus Airplanes, 24043-24045 [2017-10264]
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Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations
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 (g)(2) 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.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2015–0214, dated October 19, 2015, 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–2016–8849.
(2) For more information about this AD,
contact Vladimir Ulyanov, Aerospace
Engineer, International Branch, ANM–116,
Transport Airplane Directorate, FAA, 1601
Lind Avenue SW., Renton, WA 98057–3356;
telephone: 425–227–1138; fax: 425–227–
1149.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (m)(3) and (m)(4) of this AD.
(m) 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 A330–71–3028,
Revision 02, dated August 31, 2015.
(ii) Reserved.
(3) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EAL, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33
5 61 93 36 96; fax +33 5 61 93 45 80; email
airworthiness.A330-A340@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/ibrlocations.html.
VerDate Sep<11>2014
15:57 May 24, 2017
Jkt 241001
Issued in Renton, Washington, on May 8,
2017.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2017–10282 Filed 5–24–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9431; Directorate
Identifier 2016–NM–104–AD; Amendment
39–18897; AD 2017–10–23]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
24043
and locating Docket No. FAA–2016–
9431; 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
SUMMARY: We are adopting a new
apply to certain Airbus Model A321
airworthiness directive (AD) for certain
series airplanes. The NPRM published
Airbus Model A321 series airplanes.
in the Federal Register on December 2,
This AD was prompted by a
determination that cracks could develop 2016 (81 FR 86975). The NPRM was
prompted by a determination from
on holes at certain fuselage frame
fatigue testing on the Model A321
locations. This AD requires repetitive
airframe that cracks could develop on
inspections for cracking on holes at
holes at certain fuselage frame locations.
certain fuselage frame locations, and
The NPRM proposed to require
repairs if necessary. We are issuing this
repetitive inspections for cracking on
AD to address the unsafe condition on
holes at certain fuselage frame locations,
these products.
and repairs if necessary. We are issuing
DATES: This AD is effective June 29,
this AD to detect and correct cracking at
2017.
certain hole locations in the fuselage
The Director of the Federal Register
approved the incorporation by reference frame, which could result in reduced
structural integrity of the airplane.
of certain publications listed in this AD
The European Aviation Safety Agency
as of June 29, 2017.
(EASA), which is the Technical Agent
ADDRESSES: For service information
for the Member States of the European
identified in this final rule, contact
Union, has issued EASA Airworthiness
Airbus, Airworthiness Office—EIAS, 1
Directive 2016–0106, dated June 6, 2016
Rond Point Maurice Bellonte, 31707
(referred to after this as the Mandatory
Blagnac Cedex, France; telephone +33 5 Continuing Airworthiness Information,
61 93 36 96; fax +33 5 61 93 44 51; email or ‘‘the MCAI’’), to correct an unsafe
account.airworth-eas@airbus.com;
condition on certain Airbus Model A321
Internet https://www.airbus.com. You
series airplanes. The MCAI states:
may view this referenced service
Following a new full scale fatigue test
information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue campaign on the A321 airframe, in the
context of the A321 extended service goal, it
SW., Renton, WA. For information on
was identified that cracks could develop on
the availability of this material at the
holes at frame (FR) 35.2A between stringers
FAA, call 425–227–1221. It is also
(STR) 22 and STR 23 on right hand (RH) and
left hand (LH) sides, also on aeroplanes
available on the Internet at https://
operated in the context of design service goal.
www.regulations.gov by searching for
This condition, if not detected and
and locating Docket No. FAA–2016–
corrected, could reduce the structural
9431.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
PO 00000
Frm 00045
Fmt 4700
Sfmt 4700
integrity of the fuselage.
Prompted by these findings, Airbus
developed an inspection programme,
published in Service Bulletin (SB) A320–53–
1315 and SB A320–53–1316, each containing
instructions for a different location.
E:\FR\FM\25MYR1.SGM
25MYR1
24044
Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations
For the reasons described above, this
[EASA] AD requires repetitive special
detailed (rototest) inspections (SDI) of the
affected holes [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–
9431.
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 NPRM 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.
We do not agree with DAL’s request.
While we acknowledge that we allow
the use of later approved revisions of
service information in AMOCs, we may
not allow use of ‘‘later FAA-approved
revisions’’ in an AD when referring to
the service document. Doing so violates
Office of the Federal Register (OFR)
regulations for approval of materials
‘‘incorporated by reference,’’ as
specified in 1 CFR 51.1(f).
In general terms, we are required by
the 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 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.
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
Airbus has issued Service Bulletin
A320–53–1315, dated January 13, 2016;
and Service Bulletin A320–53–1316,
dated January 13, 2016. This service
information describes procedures for
doing a special detailed inspection for
cracking at the tooling holes on frame
35.2A between stringer 22 and stringer
23, and repairs. These documents are
distinct since they apply to different
sides of the airplane. 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
Action
Labor cost
Inspection ......
12 work-hours × $85 per hour = $1,020 per inspection cycle.
We have received no definitive data
that will 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
VerDate Sep<11>2014
15:57 May 24, 2017
Jkt 241001
Parts cost
Cost per product
$0
$1,020 per inspection
cycle.
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:
PO 00000
Frm 00046
Fmt 4700
Sfmt 4700
Cost on U.S. operators
$178,500 per inspection
cycle
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,
■
E:\FR\FM\25MYR1.SGM
25MYR1
Federal Register / Vol. 82, No. 100 / Thursday, May 25, 2017 / Rules and Regulations
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.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2017–10–23 Airbus: Amendment 39–18897;
Docket No. FAA–2016–9431; Directorate
Identifier 2016–NM–104–AD.
(a) Effective Date
This AD is effective June 29, 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 on holes
at certain fuselage frame locations. We are
issuing this AD to detect and correct cracking
at certain hole locations in the fuselage
frame, which could result in reduced
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Inspections
At the later of the times specified in
paragraphs (g)(1) and (g)(2) of this AD: Do a
special detailed (rototest) inspection for
cracking of the affected holes at frame 35.2A
on the left-hand side and right-hand side
between stringer 22 and stringer 23, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1315, dated January 13, 2016 (right-hand
side); and Airbus Service Bulletin A320–53–
1316, dated January 13, 2016 (left-hand side).
Repeat the inspection of the affected holes
thereafter at intervals not to exceed 21,500
flight cycles or 43,100 flight hours,
whichever occurs first.
(1) Before exceeding 25,400 total flight
cycles or 50,900 total flight hours since first
flight of the airplane, whichever occurs first.
(2) Within 3,300 flight cycles after the
effective date of this AD.
(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
VerDate Sep<11>2014
15:57 May 24, 2017
Jkt 241001
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 specified otherwise 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 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
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
Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2016–0106, dated
PO 00000
Frm 00047
Fmt 4700
Sfmt 4700
24045
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–
2016–9431.
(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 A320–53–1315,
dated January 13, 2016.
(ii) Airbus Service Bulletin A320–53–1316,
dated January 13, 2016.
(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/ibrlocations.html.
Issued in Renton, Washington, on May 10,
2017.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2017–10264 Filed 5–24–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0048; Directorate
Identifier 2016–CE–035–AD; Amendment
39–18876; AD 2017–10–02]
RIN 2120–AA64
Airworthiness Directives; Slingsby
Aviation Ltd. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
airworthiness directive (AD) 2015–11–
01 for Slingsby Aviation Ltd. Models
T67M260 and T67M260–T3A airplanes.
This AD results from mandatory
continuing airworthiness information
SUMMARY:
E:\FR\FM\25MYR1.SGM
25MYR1
Agencies
[Federal Register Volume 82, Number 100 (Thursday, May 25, 2017)]
[Rules and Regulations]
[Pages 24043-24045]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-10264]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9431; Directorate Identifier 2016-NM-104-AD;
Amendment 39-18897; AD 2017-10-23]
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 certain
Airbus Model A321 series airplanes. This AD was prompted by a
determination that cracks could develop on holes at certain fuselage
frame locations. This AD requires repetitive inspections for cracking
on holes at certain fuselage frame locations, and repairs if necessary.
We are issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective June 29, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 29,
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-
9431.
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-
9431; 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 certain Airbus Model A321
series airplanes. The NPRM published in the Federal Register on
December 2, 2016 (81 FR 86975). The NPRM was prompted by a
determination from fatigue testing on the Model A321 airframe that
cracks could develop on holes at certain fuselage frame locations. The
NPRM proposed to require repetitive inspections for cracking on holes
at certain fuselage frame locations, and repairs if necessary. We are
issuing this AD to detect and correct cracking at certain hole
locations in the fuselage frame, 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
Airworthiness Directive 2016-0106, dated June 6, 2016 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition on certain Airbus Model
A321 series airplanes. The MCAI states:
Following 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 holes at frame (FR) 35.2A
between stringers (STR) 22 and STR 23 on right hand (RH) and left
hand (LH) 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) A320-53-1315 and SB
A320-53-1316, each containing instructions for a different location.
[[Page 24044]]
For the reasons described above, this [EASA] AD requires
repetitive special detailed (rototest) inspections (SDI) of the
affected holes [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-
9431.
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 NPRM 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.
We do not agree with DAL's request. While we acknowledge that we
allow the use of later approved revisions of service information in
AMOCs, we may not allow use of ``later FAA-approved revisions'' in an
AD when referring to the service document. Doing so violates Office of
the Federal Register (OFR) regulations for approval of materials
``incorporated by reference,'' as specified in 1 CFR 51.1(f).
In general terms, we are required by the 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 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. 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
Airbus has issued Service Bulletin A320-53-1315, dated January 13,
2016; and Service Bulletin A320-53-1316, dated January 13, 2016. This
service information describes procedures for doing a special detailed
inspection for cracking at the tooling holes on frame 35.2A between
stringer 22 and stringer 23, and repairs. These documents are distinct
since they apply to different sides of the airplane. 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............ 12 work-hours x $85 per $0 $1,020 per inspection $178,500 per
hour = $1,020 per cycle. inspection cycle
inspection cycle.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that will 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
0
Accordingly, under the authority delegated to me by the Administrator,
[[Page 24045]]
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):
2017-10-23 Airbus: Amendment 39-18897; Docket No. FAA-2016-9431;
Directorate Identifier 2016-NM-104-AD.
(a) Effective Date
This AD is effective June 29, 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 on holes at
certain fuselage frame locations. We are issuing this AD to detect
and correct cracking at certain hole locations in the fuselage
frame, which could result in reduced structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Inspections
At the later of the times specified in paragraphs (g)(1) and
(g)(2) of this AD: Do a special detailed (rototest) inspection for
cracking of the affected holes at frame 35.2A on the left-hand side
and right-hand side between stringer 22 and stringer 23, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-53-1315, dated January 13, 2016 (right-hand side); and
Airbus Service Bulletin A320-53-1316, dated January 13, 2016 (left-
hand side). Repeat the inspection of the affected holes thereafter
at intervals not to exceed 21,500 flight cycles or 43,100 flight
hours, whichever occurs first.
(1) Before exceeding 25,400 total flight cycles or 50,900 total
flight hours since first flight of the airplane, whichever occurs
first.
(2) Within 3,300 flight cycles after the effective date of this
AD.
(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 specified otherwise 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 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 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
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA Airworthiness Directive 2016-0106, 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-2016-9431.
(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 A320-53-1315, dated January 13,
2016.
(ii) Airbus Service Bulletin A320-53-1316, dated January 13,
2016.
(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 May 10, 2017.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2017-10264 Filed 5-24-17; 8:45 am]
BILLING CODE 4910-13-P