Airworthiness Directives; Airbus Airplanes, 19925-19928 [2018-09280]
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Federal Register / Vol. 83, No. 88 / Monday, May 7, 2018 / Rules and Regulations
Issued in Kansas City, Missouri, on April
19, 2018.
Melvin Johnson,
Deputy Director, Policy and Innovation
Division, Aircraft Certification Service.
For more information about this AD,
contact William O. Herderich, Aerospace
Engineer, Atlanta ACO Branch, FAA, 1701
Columbia Avenue, College Park, Georgia
30337; phone: (404) 474–5547; fax: (404)
474–5605; email: william.o.herderich@
faa.gov.
https://www.regulations.gov by searching
for and locating Docket No. FAA–2017–
1245.
[FR Doc. 2018–08956 Filed 5–4–18; 8:45 am]
(k) Related Information
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
1245; 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 Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3223.
SUPPLEMENTARY INFORMATION:
BILLING CODE 4910–13–P
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(l) 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 the AD specifies otherwise.
(i) Gulfstream G350 Customer Bulletin
Number 192A, dated June 15, 2017, that
incorporates Appendix A, Gulfstream
Document GIV–SGER–553, Revision A,
Instructions for Continued Airworthiness for
Gulfstream Repair Drawing SE05732102,
dated December 14, 2016.
(ii) Gulfstream G450 Customer Bulletin
192A, dated June 15, 2017, that incorporates
Appendix A, Gulfstream Document GIV–
SGER–553, Revision A, Instructions for
Continued Airworthiness for Gulfstream
Repair Drawing SE05732102, dated
December 14, 2016.
(iii) Gulfstream IV Customer Bulletin
Number 238A, dated June 15, 2017, that
incorporates Appendix A, Gulfstream
Document GIV–SGER–553, Revision A,
Instructions for Continued Airworthiness for
Gulfstream Repair Drawing SE05732102,
dated December 14, 2016.
(iv) Gulfstream G300 Customer Bulletin
Number 238A, dated June 15, 2017, that
incorporates Appendix A, Gulfstream
Document GIV–SGER–553, Revision A,
Instructions for Continued Airworthiness for
Gulfstream Repair Drawing SE05732102,
dated December 14, 2016.
(v) Gulfstream G400 Customer Bulletin
Number 238A, dated June 15, 2017, that
incorporates Appendix A, Gulfstream
Document GIV–SGER–553, Revision A,
Instructions for Continued Airworthiness for
Gulfstream Repair Drawing SE05732102,
dated December 14, 2016.
(3) For Gulfstream Aerospace Corporation
service information identified in this AD,
contact Gulfstream Aerospace Corporation,
P.O. Box 2206, Savannah, Georgia 31402–
2206; telephone: (800) 810–4853; fax 912–
965–3520; email: pubs@gulfstream.com;
internet: https://www.gulfstream.com/
product_support/technical_pubs/pubs/
index.htm.
(4) You may view this service information
at FAA, Policy and Innovation Division, 901
Locust, Kansas City, Missouri 64106. For
information on the availability of this
material at the FAA, call (816) 329–4148.
(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.
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Jkt 244001
19925
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–1245; Product
Identifier 2017–NM–099–AD; Amendment
39–19266; AD 2018–09–09]
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 certain
Airbus Model A318 series airplanes and
Model A319 series airplanes; all Model
A320–211, –212, –214, –216, –231,
–232, and –233 airplanes; and all Model
A321–111, –112, –131, –211, –212,
–213, –231, and –232 airplanes. This AD
was prompted by an evaluation by the
design approval holder (DAH)
indicating that the holes of the upper
cleat to upper stringer attachments at
certain areas of the left- and right-hand
wings are subject to widespread fatigue
damage (WFD). This AD requires
modifying the holes of the upper cleat
to upper stringer attachments at certain
areas of the left- and right-hand wings.
We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective June 11,
2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of June 11, 2018.
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 Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
SUMMARY:
PO 00000
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Examining the AD Docket
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 A318
series airplanes and Model A319 series
airplanes; all Model A320–211, –212,
–214, –216, –231, –232, and –233
airplanes; and all Model A321–111,
–112, –131, –211, –212, –213, –231, and
–232 airplanes. The NPRM published in
the Federal Register on January 12,
2018 (83 FR 1579) (‘‘the NPRM’’). The
NPRM was prompted by an evaluation
by the DAH indicating that the holes of
the upper cleat to upper stringer
attachments at certain areas of the leftand right-hand wings are subject to
WFD. The NPRM proposed to require
modifying the holes of the upper cleat
to upper stringer attachments at certain
areas of the left- and right-hand wings.
We are issuing this AD to prevent
fatigue cracking in the stringer
attachment holes of the wings, which
could result in reduced structural
integrity of the wings.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2017–0117,
dated July 7, 2017 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for certain Airbus Model A318 series
airplanes and Model A319 series
E:\FR\FM\07MYR1.SGM
07MYR1
19926
Federal Register / Vol. 83, No. 88 / Monday, May 7, 2018 / Rules and Regulations
airplanes; all Model A320–211, –212,
–214, –216, –231, –232, and –233
airplanes; and all Model A321–111,
–112, –131, –211, –212, –213, –231, and
–232 airplanes. The MCAI states:
Within the scope of work of service life
extension for A320 aeroplanes and of
widespread fatigue damage evaluations, it
has been determined that a structural
modification is required to allow the
aeroplanes to continue operation up to the
limit of validity (LoV).
This condition, if not corrected, may affect
the structural integrity of the wing.
To address this potential unsafe condition,
Airbus issued [service bulletin] SB A320–57–
1208, providing instructions to oversize the
holes of the upper cleat to upper stringer
attachments at Rib 2 to Rib 7 (inclusive).
For the reason described above, this
[EASA] AD requires modification of the
affected holes.
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–2017–
1245.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment. United
Airlines agreed with the intent of the
NPRM.
Request To Clarify Applicability
Allegiant Air asked that we clarify the
manufacturer serial numbers (MSNs)
identified in the applicability section of
the proposed AD. Allegiant Air stated
that the effectivity specified in Airbus
Service Bulletin A320–57–1208, dated
November 21, 2016, identifies airplanes
up to and including MSN 7493, and
asked about airplanes having MSNs
higher than 7493. Allegiant Air noted
that it has 11 Model A320 airplanes
with MSNs outside those listed in
Airbus Service Bulletin A320–57–1208,
dated November 21, 2016. Allegiant Air
added that it understands the AD takes
precedence over the service
information, but there are several
configurations listed therein. Allegiant
Air also added that since the MSNs in
question are not listed in the effectivity
of the service information, an operator
with an MSN outside the effectivity will
not know which modification kit to
order.
We agree to clarify. The effectivity in
Airbus Service Bulletin A320–57–1208,
dated November 21, 2016, does not
include all MSNs for Model A320
airplanes, and the applicability
specified in paragraph (c) of this AD
includes all MSNs for Model A320
airplanes, except for airplanes having
certain modifications. We acknowledge
that the referenced service information
may not be adequate for certain airplane
configurations. Therefore, we have
revised paragraph (g) of this AD to
provide an option for doing the
modification, including identification of
the appropriate modification kit, using a
method approved by the Manager,
International Section, Transport
Standards Branch, FAA; or EASA; or
Airbus’s EASA Design Organization
Approval (DOA).
In addition, Airbus has informed us
that Revision 1 of the referenced service
information will expand the effectivity
to include MSNs up to 8555. Airbus has
also informed us that, upon request, it
will issue a technical adaptation as an
interim method of compliance until a
revised service bulletin is issued.
Conclusion
We reviewed the relevant data,
considered the comments 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 Airbus Service
Bulletin A320–57–1208, dated
November 21, 2016. This service
information describes procedures for
modifying the stringer attachments at
rib 2 through rib 7 of the left- and righthand wings. The modification includes
oversizing the holes, doing an eddy
current inspection of the affected holes
for damage, and repair. 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 1,136
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Modification (by oversizing and doing eddy
current inspection).
125 work-hours × $85 per hour = $10,625 ....
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition actions
specified in this AD.
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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,
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Parts cost
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
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$26,260
Cost per
product
$36,885
Cost on U.S.
operators
$41,901,360
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes to the Director of the System
Oversight Division.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
E:\FR\FM\07MYR1.SGM
07MYR1
Federal Register / Vol. 83, No. 88 / Monday, May 7, 2018 / Rules and Regulations
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
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■
VerDate Sep<11>2014
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Jkt 244001
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):
■
2018–09–09 Airbus: Amendment 39–19266;
Docket No. FAA–2017–1245; Product
Identifier 2017–NM–099–AD.
(a) Effective Date
This AD is effective June 11, 2018.
(c) Applicability
This AD applies to Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–211,
–212, –214, –216, –231, –232, and –233
airplanes; and Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes;
certificated in any category; all manufacturer
serial numbers, except airplanes specified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) Model A318 series airplanes on which
Airbus Modification (Mod) 39195 has been
embodied in production or Airbus Service
Bulletin A320–00–1219 has been embodied
in service.
(2) Model A319 series airplanes on which
Airbus Mod 28238, Mod 28162, and Mod
28342 have been embodied in production.
(d) Subject
Air Transport Association (ATA) of
America Code 57, Wings.
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Fmt 4700
This AD was prompted by an evaluation by
the design approval holder indicating that
the holes of the upper cleat to upper stringer
attachments at rib 2 through rib 7 of the leftand right-hand wings are subject to
widespread fatigue damage. We are issuing
this AD to prevent fatigue cracking in the
stringer attachment holes of the wings, which
could result in reduced structural integrity of
the wings.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(b) Affected ADs
None.
PO 00000
(e) Reason
Sfmt 4725
(g) Modification
Before reaching the upper limit, but not
before reaching the lower limit, as defined in
table 1 to paragraph (g) of this AD, as
applicable: Modify the holes of the upper
cleat to upper stringer attachments at rib 2
through rib 7 inclusive, on the left- and righthand wings by oversizing the holes, doing
eddy current inspections of the holes for
damage, and repairing any damage found
before further flight, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–57–1208, dated
November 21, 2016, except as required by
paragraph (h) of this AD; or using a method
approved by the Manager, International
Section, Transport Standards Branch, FAA;
or the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
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07MYR1
ER07MY18.026</GPH>
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.
19927
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Federal Register / Vol. 83, No. 88 / Monday, May 7, 2018 / Rules and Regulations
(h) Service Information Exception
Where Airbus Service Bulletin A320–57–
1208, dated November 21, 2016, specifies to
contact Airbus for appropriate action, and
specifies that action as ‘‘RC’’ (Required for
Compliance): Before further flight,
accomplish corrective actions in accordance
with the procedures specified in paragraph
(i)(2) of this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the International Section, send it
to the attention of the person identified in
paragraph (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
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: As of the
effective date of this AD, 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 Section, Transport
Standards Branch, FAA; or EASA; or
Airbus’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized 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.
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(j) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0117, dated July 7, 2017, 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–2017–1245.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3223.
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Jkt 244001
(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 A320–57–1208,
dated November 21, 2016.
(ii) Reserved.
(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 Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(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 Des Moines, Washington, on
April 20, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–09280 Filed 5–4–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–0838; Product
Identifier 2017–NE–33–AD; Amendment 39–
19275; AD 2018–10–01]
RIN 2120–AA64
Airworthiness Directives; Safran
Helicopter Engines, S.A., Turboshaft
Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Safran Helicopter Engines, S.A., Arriel
2E turboshaft engines. This AD was
prompted by reports of ruptured front
support pins on the accessory gearbox
front support. This AD requires
replacement of the accessory gearbox
front support. We are issuing this AD to
address the unsafe condition on these
products.
SUMMARY:
PO 00000
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Fmt 4700
Sfmt 4700
This AD becomes effective June
11, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Safran Helicopter Engines, S.A., 40220
Tarnos, France; phone: (33) 05 59 74 40
00; fax: (33) 05 59 74 45 15. You may
view this service information at the
FAA, Engine and Propeller Standards
Branch, 1200 District Avenue,
Burlington, MA. For information on the
availability of this material at the FAA,
call 781–238–7759. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0838.
DATES:
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–2017–
0838; 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 mandatory
continuing airworthiness information
(MCAI), the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
Docket Operations, 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:
Robert Green, Aerospace Engineer, ECO
Branch, FAA, 1200 District Avenue;
phone: 781–238–7754; fax: 781–238–
7199; email: robert.green@faa.gov.
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 Safran Helicopter Engines,
S.A., Arriel 2E turboshaft engines. The
NPRM published in the Federal
Register on November 3, 2017 (82 FR
51170). The NPRM was prompted by
reports of ruptured front support pins
on the accessory gearbox front support.
The NPRM proposed to require
replacement of the accessory gearbox
front support. We are issuing this AD to
address the unsafe condition on these
products.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA AD 2016–
0235, dated November 24, 2016
(referred to after this as the MCAI), to
E:\FR\FM\07MYR1.SGM
07MYR1
]]>Agencies
[Federal Register Volume 83, Number 88 (Monday, May 7, 2018)]
[Rules and Regulations]
[Pages 19925-19928]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-09280]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-1245; Product Identifier 2017-NM-099-AD; Amendment
39-19266; AD 2018-09-09]
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 A318 series airplanes and Model A319 series airplanes; all
Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and
all Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes. This AD was prompted by an evaluation by the design approval
holder (DAH) indicating that the holes of the upper cleat to upper
stringer attachments at certain areas of the left- and right-hand wings
are subject to widespread fatigue damage (WFD). This AD requires
modifying the holes of the upper cleat to upper stringer attachments at
certain areas of the left- and right-hand wings. We are issuing this AD
to address the unsafe condition on these products.
DATES: This AD is effective June 11, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of June 11,
2018.
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: [email protected];
internet: https://www.airbus.com. You may view this referenced service
information at the FAA, Transport Standards Branch, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195. It is also available on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2017-1245.
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-2017-
1245; 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 Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.
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 A318
series airplanes and Model A319 series airplanes; all Model A320-211, -
212, -214, -216, -231, -232, and -233 airplanes; and all Model A321-
111, -112, -131, -211, -212, -213, -231, and -232 airplanes. The NPRM
published in the Federal Register on January 12, 2018 (83 FR 1579)
(``the NPRM''). The NPRM was prompted by an evaluation by the DAH
indicating that the holes of the upper cleat to upper stringer
attachments at certain areas of the left- and right-hand wings are
subject to WFD. The NPRM proposed to require modifying the holes of the
upper cleat to upper stringer attachments at certain areas of the left-
and right-hand wings. We are issuing this AD to prevent fatigue
cracking in the stringer attachment holes of the wings, which could
result in reduced structural integrity of the wings.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2017-0117, dated July 7, 2017 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for certain Airbus Model A318 series airplanes and
Model A319 series
[[Page 19926]]
airplanes; all Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes; and all Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes. The MCAI states:
Within the scope of work of service life extension for A320
aeroplanes and of widespread fatigue damage evaluations, it has been
determined that a structural modification is required to allow the
aeroplanes to continue operation up to the limit of validity (LoV).
This condition, if not corrected, may affect the structural
integrity of the wing.
To address this potential unsafe condition, Airbus issued
[service bulletin] SB A320-57-1208, providing instructions to
oversize the holes of the upper cleat to upper stringer attachments
at Rib 2 to Rib 7 (inclusive).
For the reason described above, this [EASA] AD requires
modification of the affected holes.
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-2017-
1245.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment. United Airlines agreed with the
intent of the NPRM.
Request To Clarify Applicability
Allegiant Air asked that we clarify the manufacturer serial numbers
(MSNs) identified in the applicability section of the proposed AD.
Allegiant Air stated that the effectivity specified in Airbus Service
Bulletin A320-57-1208, dated November 21, 2016, identifies airplanes up
to and including MSN 7493, and asked about airplanes having MSNs higher
than 7493. Allegiant Air noted that it has 11 Model A320 airplanes with
MSNs outside those listed in Airbus Service Bulletin A320-57-1208,
dated November 21, 2016. Allegiant Air added that it understands the AD
takes precedence over the service information, but there are several
configurations listed therein. Allegiant Air also added that since the
MSNs in question are not listed in the effectivity of the service
information, an operator with an MSN outside the effectivity will not
know which modification kit to order.
We agree to clarify. The effectivity in Airbus Service Bulletin
A320-57-1208, dated November 21, 2016, does not include all MSNs for
Model A320 airplanes, and the applicability specified in paragraph (c)
of this AD includes all MSNs for Model A320 airplanes, except for
airplanes having certain modifications. We acknowledge that the
referenced service information may not be adequate for certain airplane
configurations. Therefore, we have revised paragraph (g) of this AD to
provide an option for doing the modification, including identification
of the appropriate modification kit, using a method approved by the
Manager, International Section, Transport Standards Branch, FAA; or
EASA; or Airbus's EASA Design Organization Approval (DOA).
In addition, Airbus has informed us that Revision 1 of the
referenced service information will expand the effectivity to include
MSNs up to 8555. Airbus has also informed us that, upon request, it
will issue a technical adaptation as an interim method of compliance
until a revised service bulletin is issued.
Conclusion
We reviewed the relevant data, considered the comments 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 Airbus Service Bulletin A320-57-1208, dated
November 21, 2016. This service information describes procedures for
modifying the stringer attachments at rib 2 through rib 7 of the left-
and right-hand wings. The modification includes oversizing the holes,
doing an eddy current inspection of the affected holes for damage, and
repair. 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 1,136 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Modification (by oversizing and 125 work-hours x $85 per $26,260 $36,885 $41,901,360
doing eddy current inspection). hour = $10,625.
----------------------------------------------------------------------------------------------------------------
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.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes to
the Director of the System Oversight Division.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on
[[Page 19927]]
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):
2018-09-09 Airbus: Amendment 39-19266; Docket No. FAA-2017-1245;
Product Identifier 2017-NM-099-AD.
(a) Effective Date
This AD is effective June 11, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A318-111, -112, -121, and -122
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes; certificated in any category; all
manufacturer serial numbers, except airplanes specified in
paragraphs (c)(1) and (c)(2) of this AD.
(1) Model A318 series airplanes on which Airbus Modification
(Mod) 39195 has been embodied in production or Airbus Service
Bulletin A320-00-1219 has been embodied in service.
(2) Model A319 series airplanes on which Airbus Mod 28238, Mod
28162, and Mod 28342 have been embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 57, Wings.
(e) Reason
This AD was prompted by an evaluation by the design approval
holder indicating that the holes of the upper cleat to upper
stringer attachments at rib 2 through rib 7 of the left- and right-
hand wings are subject to widespread fatigue damage. We are issuing
this AD to prevent fatigue cracking in the stringer attachment holes
of the wings, which could result in reduced structural integrity of
the wings.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Modification
Before reaching the upper limit, but not before reaching the
lower limit, as defined in table 1 to paragraph (g) of this AD, as
applicable: Modify the holes of the upper cleat to upper stringer
attachments at rib 2 through rib 7 inclusive, on the left- and
right-hand wings by oversizing the holes, doing eddy current
inspections of the holes for damage, and repairing any damage found
before further flight, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-57-1208, dated November
21, 2016, except as required by paragraph (h) of this AD; or using a
method approved by the Manager, International Section, Transport
Standards Branch, FAA; or the European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.
[GRAPHIC] [TIFF OMITTED] TR07MY18.026
[[Page 19928]]
(h) Service Information Exception
Where Airbus Service Bulletin A320-57-1208, dated November 21,
2016, specifies to contact Airbus for appropriate action, and
specifies that action as ``RC'' (Required for Compliance): Before
further flight, accomplish corrective actions in accordance with the
procedures specified in paragraph (i)(2) of this AD.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Section, send it to the attention of
the person identified in paragraph (j)(2) of this AD. Information
may be emailed to [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: As of the effective date of
this AD, 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 Section, Transport Standards
Branch, 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 2017-0117, dated July 7, 2017, 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-2017-1245.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3223.
(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 A320-57-1208, dated November 21,
2016.
(ii) Reserved.
(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: [email protected]; internet:
https://www.airbus.com.
(4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
(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 Des Moines, Washington, on April 20, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-09280 Filed 5-4-18; 8:45 am]
BILLING CODE 4910-13-P
