Airworthiness Directives; Airbus Airplanes, 3871-3876 [2015-01257]
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Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations
agency may not conduct or sponsor, and a
person is not required to respond to, nor
shall a person be subject to a penalty for
failure to comply with a collection of
information subject to the requirements of
the Paperwork Reduction Act unless that
collection of information displays a current
valid OMB Control Number. The OMB
Control Number for this information
collection is 2120–0056. Public reporting for
this collection of information is estimated to
be approximately 5 minutes per response,
including the time for reviewing instructions,
completing and reviewing the collection of
information. All responses to this collection
of information are mandatory. Comments
concerning the accuracy of this burden and
suggestions for reducing the burden should
be directed to the FAA at: 800 Independence
Ave. SW., Washington, DC 20591, Attn:
Information Collection Clearance Officer,
AES–200.
(h) Related Information
Refer to MCAI Federal Office of Civil
Aviation (FOCA) AD HB–2014–001, dated
July 25, 2014; and AD HB–2014–001R1,
dated November 5, 2014 for related
information. The MCAI can be found in the
AD docket on the Internet at: https://
www.regulations.gov/
#!docketBrowser;rpp=25;po=0;dct=PR%25
2BSR;D=FAA-2014-0770.
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(i) 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) Pilatus Aircraft Ltd. Pilatus PC–7
Service Bulletin No: 51–001, Revision No. 1,
dated August 26, 2014.
(ii) Reserved.
(3) For Pilatus Aircraft Ltd. service
information identified in this AD, contact
Pilatus Aircraft Ltd., Customer Technical
Support (MCC), P.O. Box 992, CH–6371
Stans, Switzerland; phone: +41 (0)41 619 67
74; fax: +41 (0)41 619 67 73; email:
Techsupport@pilatus-aircraft.com; internet:
https://www.pilatus-aircraft.com.
(4) You may view this service information
at the FAA, Small Airplane Directorate, 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.
Issued in Kansas City, Missouri, on
December 31, 2014.
Robert Busto,
Acting Manager, Small Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–00010 Filed 1–23–15; 8:45 am]
BILLING CODE 4910–13–P
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0692; Directorate
Identifier 2012–NM–024–AD; Amendment
39–18031; AD 2014–23–15]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) AD 2011–
14–06 for all Airbus Model A318, A319,
A320, and A321 series airplanes. AD
2011–14–06 required revising the
maintenance program. This new AD
requires revising the maintenance
program to incorporate new, more
restrictive limitations. This AD was
prompted by the determination that
more restrictive limitations are
necessary. We are issuing this AD to
prevent fatigue cracking, accidental
damage, or corrosion in principal
structural elements, and possible failure
of certain life limited parts, which could
result in reduced structural integrity of
the airplane.
DATES: This AD becomes effective
March 2, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of March 2, 2015.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of August 22, 2011 (76 FR
42024, July 18, 2011).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of November 7, 2007 (72 FR
56262, October 3, 2007).
ADDRESSES: You may examine the AD
docket on the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2013-0692; or in
person at the 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.
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.airworthSUMMARY:
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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.
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 supplemental notice of
proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD
2011–14–06, Amendment 39–16741 (76
FR 42024, July 18, 2011). AD 2011–14–
06 applied to Airbus Model A318, A319,
A320, and A321 series airplanes. The
SNPRM published in the Federal
Register on May 28, 2014 (79 FR 30492).
We preceded the SNPRM with a notice
of proposed rulemaking (NPRM) that
published in the Federal Register on
August 13, 2013 (78 FR 49213).
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2013–0147,
dated July 16, 2013 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus Model A318, A319, A320,
and A321 series airplanes. The MCAI
states:
The airworthiness limitations for Airbus
A320 family aeroplanes are currently
included in Airbus A318/A319/A320/A321
Airworthiness Limitations Section (ALS)
document. The airworthiness limitations
applicable to the Damage Tolerant
Airworthiness Limitation Items (DT ALI) are
currently given in Airbus ALS Part 2, which
is approved by EASA.
Previously, EASA issued AD 2010–0071R1
[https://ad.easa.europa.eu/blob/easa_ad_
2010_0071_R1.pdf/AD_2010–0071R1_1]
[associated with FAA AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011)], which required the implementation of
the DT ALI maintenance instructions as
specified in Airbus A318/A319/A320/A321
ALI Document ref. AI/SE–M4/95A.0252/96
issue 10 and Airbus A319 Corporate Jet ALI
Document ref. AI/SE–M2/95A.1038/99.
The new Airbus A318/A319/A320/A321
ALS Part 2 Revision 02, which includes also
Airbus A319 Corporate Jet, introduces more
restrictive DT ALI maintenance instructions.
Failure to comply with these instructions
could result in an unsafe condition.
Application of new DT ALI tasks 531129–
02–2 and 531129–02–3 introduces initial and
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repetitive inspections of the windshield
central lower node continuity fittings,
replacing the one time inspection for that
subject, previously required by EASA AD
2011–0231 [https://ad.easa.europa.eu/blob/
easa_ad_2011_0231.pdf] [associated with
FAA AD 2013–13–03, Amendment 39–17491
(78 FR 41280, July 10, 2013)].
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2010–0071R1 * * *, which are
superseded, and requires compliance with all
maintenance tasks as described in Airbus
A318/A319/A320/A321 ALS part 2 at
Revision 02.
The unsafe condition is fatigue cracking,
accidental damage, or corrosion in
principal structural elements, and
possible failure of certain life limited
parts, which could result in reduced
structural integrity of the airplane. You
may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov/
#!documentDetail;D=FAA-2013-0002.
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Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the SNPRM (79 FR 30492,
May 28, 2014) and the FAA’s response
to each comment.
Request To Extend Compliance Time
United Airlines (UAL), Delta Airlines
(DAL), and Virgin America asked that
we extend the compliance time for
incorporation of Airbus A318/A319/
A320/A321 ALS Part 2—DamageTolerant Airworthiness Limitation Items
(DT ALI), Revision 02, dated May 28,
2013. UAL stated that it would like to
manage the task incorporation on an
individual basis. UAL proposed that we
revise the compliance times specified in
paragraph (n) of the SNPRM (79 FR
30492, May 28, 2014) as follows: ‘‘After
the effective date of this AD, incorporate
each task into the program within the
specific threshold/interval provided.’’
DAL and Virgin America stated that, to
provide time to revise the maintenance
program and perform any related tasks
that might exceed the compliance
thresholds specified in the ALI, the
grace period specified in paragraph (n)
of the SNPRM should be changed from
4 to 12 months.
DAL asked for more time to update
the maintenance program to incorporate
Airbus A318/A319/A320/A321 ALS
Part 2—Damage-Tolerant Airworthiness
Limitation Items (DT ALI), Revision 02,
dated May 28, 2013. DAL and Virgin
America requested 9 months, as
opposed to 30 days, because 9 months
was the allowed compliance time for
incorporating airworthiness limitation
items into the maintenance program
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required by AD 2011–14–06,
Amendment 39–16741 (76 FR 42024,
July 18, 2011).
We acknowledge the commenters’
concerns; however, we do not agree to
extend the compliance times for
incorporation of the tasks into the
maintenance program. We based the
compliance times in this AD primarily
on our assessment of the safety risk.
Since some safety issues are more timesensitive than others, we consider the
overall risk to the fleet, including the
severity of the failure and the likelihood
of the occurrence of the failure. In this
case, the primary reason for requiring
incorporation of Airbus A318/A319/
A320/A321 ALS Part 2—DamageTolerant Airworthiness Limitation Items
(DT ALI), Revision 02, dated May 28,
2013, is to cover extension of the design
service goal and preliminary results
from widespread fatigue damage.
Therefore, we do not agree to extend
the grace period or compliance times for
incorporation of the tasks into the
maintenance program. However, under
the provisions of paragraph (p)(1) of this
AD, we will consider requests for
approval of extending the compliance
time based on the current status of the
maintenance and inspection programs
relative to the ALI tasks if sufficient data
are submitted to substantiate that it
would provide an acceptable level of
safety. We have not changed this AD in
this regard.
‘‘Contacting the Manufacturer’’
Paragraph in This AD
Since late 2006, we have included a
standard paragraph titled ‘‘Airworthy
Product’’ in all MCAI ADs in which the
FAA develops an AD based on a foreign
authority’s AD.
We have become aware that some
operators have misunderstood or
misinterpreted the Airworthy Product
paragraph to allow the owner/operator
to use messages provided by the
manufacturer as approval of deviations
during the accomplishment of an ADmandated action. The Airworthy
Product paragraph does not approve
messages or other information provided
by the manufacturer for deviations to
the requirements of the AD-mandated
actions. The Airworthy Product
paragraph only addresses the
requirement to contact the manufacturer
for corrective actions for the identified
unsafe condition and does not cover
deviations from other AD requirements.
However, deviations to AD-required
actions are addressed in 14 CFR 39.17,
and anyone may request the approval
for an alternative method of compliance
to the AD-required actions using the
procedures found in 14 CFR 39.19.
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To address this misunderstanding and
misinterpretation of the Airworthy
Product paragraph, we have changed the
paragraph and retitled it ‘‘Contacting the
Manufacturer.’’ This paragraph now
clarifies that for any requirement in this
AD to obtain corrective actions from a
manufacturer, the actions must be
accomplished using a method approved
by the FAA, the European Aviation
Safety Agency (EASA), or Airbus’s
EASA Design Organization Approval
(DOA).
The Contacting the Manufacturer
paragraph also clarifies that, if approved
by the DOA, the approval must include
the DOA-authorized signature. The DOA
signature indicates that the data and
information contained in the document
are EASA-approved, which is also FAAapproved. Messages and other
information provided by the
manufacturer that do not contain the
DOA-authorized signature approval are
not EASA-approved, unless EASA
directly approves the manufacturer’s
message or other information.
This clarification does not remove
flexibility previously afforded by the
Airworthy Product paragraph.
Consistent with long-standing FAA
policy, such flexibility was never
intended for required actions. This is
also consistent with the
recommendation of the Airworthiness
Directive Implementation Aviation
Rulemaking Committee to increase
flexibility in complying with ADs by
identifying those actions in
manufacturers’ service instructions that
are ‘‘Required for Compliance’’ with
ADs. We continue to work with
manufacturers to implement this
recommendation. But once we
determine that an action is required, any
deviation from the requirement must be
approved as an alternative method of
compliance.
We also have decided not to include
a generic reference to either the
‘‘delegated agent’’ or ‘‘design approval
holder (DAH) with State of Design
Authority design organization
approval,’’ but instead we have
provided the specific delegation
approval granted by the State of Design
Authority for the DAH.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the SNPRM (79 FR
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30492, May 28, 2014) for correcting the
unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the SNPRM (79 FR 30492,
May 28, 2014).
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Costs of Compliance
We estimate that this AD affects 851
airplanes of U.S. registry.
The actions required by AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011), and retained in
this AD take about 1 work-hour per
product, at an average labor rate of $85
per work-hour. Based on these figures,
the estimated cost of the required
actions is $85 per product.
We also estimate that it will take
about 1 work-hour per product to
comply with the new basic
requirements of this AD. The average
labor rate is $85 per work-hour. Based
on these figures, we estimate the cost of
this AD on U.S. operators to be $72,335,
or $85 per product.
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.
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Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
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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.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2013-0692; 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 Operations office (telephone
800–647–5527) is in the ADDRESSES
section.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2011–14–06, Amendment 39–16741 (76
FR 42024, July 18, 2011), and adding the
following new AD:
■
2014–23–15 Airbus: Amendment 39–18031.
Docket No. FAA–2013–0692; Directorate
Identifier 2012–NM–024–AD.
(a) Effective Date
This AD becomes effective March 2, 2015.
(b) Affected ADs
This AD replaces AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011).
(c) Applicability
This AD applies to all Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–111,
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–211, –212, –214, –231, –232, and –233
airplanes; and Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 05, Periodic Inspections.
(e) Reason
This AD was prompted by a determination
that more restrictive limitations are
necessary. We are issuing this AD to prevent
fatigue cracking, accidental damage, or
corrosion in principal structural elements,
and possible failure of certain life limited
parts, 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) Retained Revision of Airworthiness
Limitations Section (ALS) To Incorporate
Safe Life Airworthiness Limitation Items
(ALIs)
This paragraph restates the requirements of
paragraph (g) of AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011). For Model A318–111 and –112
airplanes; Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes;
Model A320–111, –211, –212, –214, –231,
–232, and –233 airplanes; and Model A321–
111, –112, –131, –211, –212, –213, –231, and
–232 airplanes: Within 3 months after
November 7, 2007 (the effective date of AD
2007–20–05, Amendment 39–15215 (72 FR
56262, October 3, 2007)), revise the ALS of
the Instructions for Continued Airworthiness
to incorporate Sub-part 1–2, ‘‘Life Limits,’’
and Sub-part 1–3, ‘‘Demonstrated Fatigue
Lives,’’ of Airbus A318/A319/A320/A321
ALS Part 1—Safe Life Airworthiness
Limitation Items, Revision 00, dated
February 28, 2006. Accomplish the actions in
Sub-part 1–2, ‘‘Life Limits,’’ and Sub-part 1–
3, ‘‘Demonstrated Fatigue Lives,’’ of Airbus
A318/A319/A320/A321 ALS Part 1—Safe
Life Airworthiness Limitation Items,
Revision 00, dated February 28, 2006, at the
times specified in Sub-part 1–2, ‘‘Life
Limits,’’ and Sub-part 1–3, ‘‘Demonstrated
Fatigue Lives,’’ of Airbus A318/A319/A320/
A321 ALS Part 1—Safe Life Airworthiness
Limitation Items, dated February 28, 2006,
except as provided by paragraph (i) of this
AD. Accomplishing the actions required by
paragraph (j) of this AD terminates the
requirements of this paragraph.
(h) Retained Revision to ALS To Incorporate
Damage Tolerant ALIs
This paragraph restates certain provisions
of paragraph (h) of AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011). For Model A318–111 and –112
airplanes; Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes;
Model A320–111, –211, –212, –214, –231,
–232, and –233 airplanes; and Model A321–
111, –112, –131, –211, –212, –213, –231, and
–232 airplanes; except Model A319 airplanes
on which Airbus Modifications 28238,
28162, and 28342 have been incorporated in
production: Within 14 days after November
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7, 2007 (the effective date of AD 2007–20–05,
Amendment 39–15215 (72 FR 56262, October
3, 2007)), revise the ALS of the Instructions
for Continued Airworthiness to incorporate
Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 7, dated
December 2005 (approved by the European
Aviation Safety Agency (EASA) on February
7, 2006); Issue 08, dated March 2006
(approved by the EASA on January 4, 2007);
or Issue 09, dated November 2006 (approved
by the EASA on May 21, 2007). Accomplish
the actions in Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 7, dated
December 2005; Issue 08, dated March 2006;
or Issue 09, dated November 2006; at the
times specified in Airbus A318/A319/A320/
A321 Airworthiness Limitation Items,
Document AI/SE–M4/95A.0252/96, Issue 7,
dated December 2005; Issue 08, dated March
2006; or Issue 09, dated November 2006; as
applicable; except as provided by paragraph
(i) of this AD. Accomplishing the actions
required by paragraph (j) or (n) of this AD,
as applicable, terminates the requirements of
this paragraph.
(i) Retained Grace Period for New or More
Restrictive Actions
This paragraph restates certain provisions
of paragraph (i) of AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011). For Model A318–111 and –112
airplanes; Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes;
Model A320–111, –211, –212, –214, –231,
–232, and –233 airplanes; and Model A321–
111, –112, –131, –211, –212, –213, –231, and
–232 airplanes: For any new or more
restrictive life-limit introduced with Sub-part
1–2, ‘‘Life Limits,’’ and Sub-part 1–3,
‘‘Demonstrated Fatigue Lives,’’ of Airbus
A318/A319/A320/A321 ALS Part 1—Safe
Life Airworthiness Limitation Items,
Revision 00, dated February 28, 2006, replace
the part at the time specified in Sub-part 1–
2, ‘‘Life Limits,’’ and Sub-part 1–3,
‘‘Demonstrated Fatigue Lives,’’ of Airbus
A318/A319/A320/A321 ALS Part 1—Safe
Life Airworthiness Limitation Items,
Revision 00, dated February 28, 2006, or
within 6 months after November 7, 2007 (the
effective date of AD 2007–20–05,
Amendment 39–15215 (72 FR 56262, October
3, 2007)), whichever is later. Accomplishing
the actions required by paragraph (n) of this
AD terminates the requirements of this
paragraph.
(j) Retained Revision of ALS To Incorporate
Damage-Tolerant ALIs With Revised
Compliance Times
This paragraph restates the requirements of
paragraph (j) of AD 2011–14–06, Amendment
39–16741 (76 FR 42024, July 18, 2011), with
revised compliance times. Within 9 months
after August 22, 2011 (the effective date of
AD 2011–14–06): Revise the maintenance
program by incorporating all maintenance
requirements and associated airworthiness
limitations specified in the Airbus A318/
A319/A320/A321 Airworthiness Limitation
Items, Document AI/SE–M4/95A.0252/96,
Issue 10, dated October 2009; or Issue 11,
dated September 2010. Comply with all
applicable maintenance requirements and
associated airworthiness limitations included
in Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 10, dated
October 2009; or Issue 11, dated September
2010; except as provided by paragraph (k) of
this AD. Accomplishing the actions required
by this paragraph terminates the
requirements of paragraph (h) of this AD.
Accomplishing the actions required by
paragraph (n) of this AD terminates the
requirements of this paragraph.
(k) Retained Special Compliance Times for
Certain Tasks
This paragraph restates the requirements of
paragraph (k) of AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011), with changes to table 1 to paragraph
(k) of this AD. For new and more restrictive
tasks introduced with Airbus A318/A319/
A320/A321 Airworthiness Limitation Items,
Document AI/SE–M4/95A.0252/96, Issue 10,
dated October 2009; or Issue 11, dated
September 2010; as specified in table 1 to
paragraph (k) of this AD: The initial
compliance time for doing the tasks is
specified in table 1 to paragraph (k) of this
AD. Accomplishing the actions required by
paragraph (n) of this AD terminates the
requirements of this paragraph.
TABLE 1 TO PARAGRAPH (K) OF THIS AD—COMPLIANCE TIMES FOR TASKS
Applicability
(as specified in the applicability column
of the task)
545102–01–6 ..........
Group 19–1A CFM, Group 19–1B
CFM, and Model A320-200 airplanes
with CFM Industrial (CFM)/International Aero Engine (IAE) engines.
545102–01–7 ..........
Model A320–100 series airplanes .......
572050–01–1 or alternative task
572050-02–1.
tkelley on DSK3SPTVN1PROD with RULES
Task
Group 19-1A and Group 19–1B airplanes.
572050–01–4 or alternative task
572050-02–4.
Model A320–200 series airplanes .......
VerDate Sep<11>2014
17:58 Jan 23, 2015
Jkt 235001
PO 00000
Frm 00010
Compliance time, whichever occurs later
The threshold as defined in Airbus
A318/A319/A320/A321 Airworthiness
Limitation Items, Document AI/
SE-M4/95A.0252/96, Issue 10, dated
October 2009; or Issue 11, dated
September 2010.
The threshold as defined in Airbus
A318/A319/A320/A321 Airworthiness
Limitation Items, Document AI/
SE-M4/95A.0252/96, Issue 10, dated
October 2009; or Issue 11, dated
September 2010.
At the time of the next due accomplishment of any one of the tasks
572004, 572020, or 572053 as currently described in the Airbus A318/
A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/
95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March
2006; or Issue 09, dated November
2006.
At the time of the next due accomplishment of any one of the tasks
572004, 572020, or 572053 as currently described in the Airbus A318/
A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/
95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March
2006; or Issue 09, dated November
2006.
Fmt 4700
Sfmt 4700
E:\FR\FM\26JAR1.SGM
Within 2,000 flight cycles or 5,500
flight hours, after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)), whichever
occurs first.
Within 2,000 flight cycles or 2,000
flight hours, after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)), whichever
occurs first.
Within 6 months after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)).
Within 6 months after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)).
26JAR1
Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations
3875
TABLE 1 TO PARAGRAPH (K) OF THIS AD—COMPLIANCE TIMES FOR TASKS—Continued
Task
572050–01–5 or alternative task
572050-02–5.
Group 21-1A airplanes .........................
572050–01–7 or alternative task
572050-02–7.
Model A320–100 series airplanes .......
534132–01–1 ..........
Model A320 PRE 30748 airplanes ......
531118–01–1 ..........
Model A318 (except (A318–121 and
-122), Group 19–1A, Group 19–1B,
and Model A320 and A321 series
airplanes.
The threshold/interval as defined in
Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue
10, dated October 2009; or Issue
11, dated September 2010.
531118–01–1 ..........
Model A318–121 and -122 airplanes ...
The threshold/interval as defined in
Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue
10, dated October 2009; or Issue
11, dated September 2010.
tkelley on DSK3SPTVN1PROD with RULES
Note 1 to table 1 to paragraph (k) of this
AD: ALI Task 572050 refers to the outer wing
dry bay and is comprised of extracts from
three ALI Tasks 572004, 572020, and 572053.
The threshold of ALI Task 572050 for the
whole dry bay area is that of the lowest
threshold of the source ALI tasks, i.e., that of
ALI Task 572053.
(l) Retained Limitation: No Alternative Life
Limits, Inspections, or Inspection Intervals
After Accomplishment of the Actions
Specified in Paragraphs (g) and (h) of This
AD
This paragraph restates the requirements of
paragraph (l) of AD 2011–14–06, Amendment
39–16741 (76 FR 42024, July 18, 2011). After
VerDate Sep<11>2014
17:58 Jan 23, 2015
Jkt 235001
At the time of the next due accomplishment of any one of the tasks
572004, 572020, or 572053 as currently described in the Airbus A318/
A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/
95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March
2006; or Issue 09, dated November
2006.
At the time of the next due accomplishment of any one of the tasks
572004, 572020, or 572053 as currently described in the Airbus A318/
A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/
95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March
2006; or Issue 09, dated November
2006.
The threshold/interval as defined in
Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue
10, dated October 2009; or Issue
11, dated September 2010.
the actions specified in paragraphs (g) and (h)
of this AD have been accomplished, no
alternative life limits, inspections, or
inspection intervals may be used, except as
provided by paragraphs (i) and (m) of this
AD, and except as required by paragraphs (j)
and (n) of this AD.
(m) Retained Limitation: No Alternative Life
Limits, Inspections, or Inspection Intervals
After Accomplishment of the Actions
Specified in Paragraph (j) of This AD
This paragraph restates the requirements of
paragraph (m) of AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011). After the actions specified in
paragraph (j) of this AD have been
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
Within 6 months after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)).
Within 6 months after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)).
Within 100 days after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)), without exceeding the previous threshold/interval as defined in Airbus A318/A319/
A320/A321 Airworthiness Limitation
Items,
Document
AI/SE-M4/
95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March
2006; or Issue 09, dated November
2006.
Within 100 days after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)), without exceeding the previous threshold/interval as defined in Airbus A318/A319/
A320/A321 Airworthiness Limitation
Items,
Document
AI/SE-M4/
95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March
2006; or Issue 09, dated November
2006.
Within 100 days after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)).
accomplished, no alternative life limits,
inspections, or inspection intervals may be
used, except as required by paragraph (n) of
this AD.
(n) New Maintenance or Inspection Program
Revision
Within 30 days after the effective date of
this AD, revise the maintenance or inspection
program, as applicable, to incorporate the
ALIs specified in paragraphs (n)(1), (n)(2),
and (n)(3) of this AD. The initial compliance
time for accomplishing the actions is at the
applicable time specified in the ALIs
specified in paragraphs (n)(1), (n)(2), and
(n)(3) of this AD; or within 4 months after the
effective date of this AD; whichever occurs
E:\FR\FM\26JAR1.SGM
26JAR1
3876
Federal Register / Vol. 80, No. 16 / Monday, January 26, 2015 / Rules and Regulations
later. Accomplishing these actions terminates
the requirements of paragraphs (g), (h), (i), (j),
and (k) of this AD.
(1) Airbus A318/A319/A320/A321 ALS
Part 1—Safe Life Airworthiness Limitation
Items, Revision 02, dated May 13, 2011.
(2) Airbus A318/A319/A320/A321 ALS
Part 2—Damage-Tolerant Airworthiness
Limitation Items (DT ALI), Revision 02, dated
May 28, 2013.
(3) Airbus A318/A319/A320/A321 ALS
Part 4—Ageing Systems Maintenance, dated
January 8, 2008.
tkelley on DSK3SPTVN1PROD with RULES
(o) New Limitation: No Alternative Actions,
Intervals, and/or Critical Design
Configuration Control Limitations (CDCCLs)
After accomplishing the revision required
by paragraph (n) of this AD, no alternative
actions (e.g., inspections), intervals, and/or
CDCCLs may be used unless the actions,
intervals, and/or CDCCLs are approved as an
alternative method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (p)(1) of this AD.
(p) 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.
(i) 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. The AMOC
approval letter must specifically reference
this AD.
(ii) AMOCs approved previously for AD
2011–14–06, Amendment 39–16741 (76 FR
42024, July 18, 2011), are approved as
AMOCs for the corresponding actions
specified in this AD.
(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 Branch, ANM–
116, Transport Airplane Directorate, 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.
(q) Related Information
Refer to Mandatory Continuing
Airworthiness Information (MCAI) European
Aviation Safety Agency Airworthiness
Directives 2012–0008, dated January 16,
VerDate Sep<11>2014
17:58 Jan 23, 2015
Jkt 235001
2012; and 2013–0147, dated July 16, 2013; for
related information. You may examine the
MCAI in the AD docket on the Internet at
https://www.regulations.gov/#!document
Detail;D=FAA-2013-0692-0002.
(r) 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 A318/A319/A320/A321 ALS Part
1—Safe Life Airworthiness Limitation Items,
Revision 02, dated May 13, 2011. The
revision level of this document is identified
on only the title page and in the Record of
Revisions. The revision date is not identified
on the title page of this document.
(ii) Airbus A318/A319/A320/A321 ALS
Part 2—Damage-Tolerant Airworthiness
Limitation Items (DT ALI), Revision 02, dated
May 28, 2013. The revision date of this
document is not identified on the title page
of this document.
(iii) Airbus A318/A319/A320/A321 ALS
Part 4—Ageing Systems Maintenance, dated
January 8, 2008. The revision date of this
document is not identified on the title page
of this document.
(3) The following service information was
approved for IBR on August 22, 2011 (76 FR
42024, July 18, 2011).
(i) Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 10, dated
October 2009. The revision level of this
document is identified on only the title page
and in the Record of Revisions.
(ii) Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 11, dated
September 2010. The revision level of this
document is identified on only the title page
and in the Record of Revisions.
(4) The following service information was
approved for IBR on November 7, 2007 (72
FR 56262, October 3, 2007).
(i) Airbus A318/A319/A320/A321 ALS Part
1—Safe Life Airworthiness Limitation Items,
Revision 00, dated February 28, 2006.
(ii) Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 7, dated
December 2005 (approved by the European
Aviation Safety Agency (EASA) on February
7, 2006).
Note 2 to paragraph (r)(4)(ii) of this AD:
This document contains the following errors:
The Summary of Changes is comprised of 11
pages, which are all identified as Page 2—
LEP of Section LEP instead of Page 1—SOC
[through] Page 11—SOC of Section SOC; the
List of Effective Pages only refers to Page 1—
SOC for the Summary of Changes. The List
of Effective Pages is comprised of two pages,
and both of those pages are identified as Page
2—LEP. The first page of Section 2 is
identified as Page 6 of Section 1 and is not
referred to in the List of Effective Pages.
(iii) Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 08, dated
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
March 2006 (approved by the EASA on
January 4, 2007).
(iv) Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 09, dated
November 2006 (approved by the EASA on
May 21, 2007).
(5) 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.
(6) 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.
(7) 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
December 23, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2015–01257 Filed 1–23–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 97
[Docket No. 30996; Amdt. No. 3624]
Standard Instrument Approach
Procedures, and Takeoff Minimums
and Obstacle Departure Procedures;
Miscellaneous Amendments
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
This rule amends, suspends,
or removes Standard Instrument
Approach Procedures (SIAPs) and
associated Takeoff Minimums and
Obstacle Departure Procedures for
operations at certain airports. These
regulatory actions are needed because of
the adoption of new or revised criteria,
or because of changes occurring in the
National Airspace System, such as the
commissioning of new navigational
facilities, adding new obstacles, or
changing air traffic requirements. These
changes are designed to provide for the
safe and efficient use of the navigable
airspace and to promote safe flight
operations under instrument flight rules
at the affected airports.
DATES: This rule is effective January 26,
2015. The compliance date for each
SUMMARY:
E:\FR\FM\26JAR1.SGM
26JAR1
]]>Agencies
[Federal Register Volume 80, Number 16 (Monday, January 26, 2015)]
[Rules and Regulations]
[Pages 3871-3876]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2015-01257]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0692; Directorate Identifier 2012-NM-024-AD;
Amendment 39-18031; AD 2014-23-15]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) AD 2011-14-06
for all Airbus Model A318, A319, A320, and A321 series airplanes. AD
2011-14-06 required revising the maintenance program. This new AD
requires revising the maintenance program to incorporate new, more
restrictive limitations. This AD was prompted by the determination that
more restrictive limitations are necessary. We are issuing this AD to
prevent fatigue cracking, accidental damage, or corrosion in principal
structural elements, and possible failure of certain life limited
parts, which could result in reduced structural integrity of the
airplane.
DATES: This AD becomes effective March 2, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 2,
2015.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of August
22, 2011 (76 FR 42024, July 18, 2011).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
November 7, 2007 (72 FR 56262, October 3, 2007).
ADDRESSES: You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-0692; or in person at the
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.
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. 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.
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 supplemental notice of proposed rulemaking (SNPRM) to
amend 14 CFR part 39 to supersede AD 2011-14-06, Amendment 39-16741 (76
FR 42024, July 18, 2011). AD 2011-14-06 applied to Airbus Model A318,
A319, A320, and A321 series airplanes. The SNPRM published in the
Federal Register on May 28, 2014 (79 FR 30492). We preceded the SNPRM
with a notice of proposed rulemaking (NPRM) that published in the
Federal Register on August 13, 2013 (78 FR 49213).
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0147, dated July 16, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A318, A319, A320, and A321 series airplanes. The MCAI states:
The airworthiness limitations for Airbus A320 family aeroplanes
are currently included in Airbus A318/A319/A320/A321 Airworthiness
Limitations Section (ALS) document. The airworthiness limitations
applicable to the Damage Tolerant Airworthiness Limitation Items (DT
ALI) are currently given in Airbus ALS Part 2, which is approved by
EASA.
Previously, EASA issued AD 2010-0071R1 [https://ad.easa.europa.eu/blob/easa_ad_2010_0071_R1.pdf/AD_2010-0071R1_1]
[associated with FAA AD 2011-14-06, Amendment 39-16741 (76 FR 42024,
July 18, 2011)], which required the implementation of the DT ALI
maintenance instructions as specified in Airbus A318/A319/A320/A321
ALI Document ref. AI/SE-M4/95A.0252/96 issue 10 and Airbus A319
Corporate Jet ALI Document ref. AI/SE-M2/95A.1038/99.
The new Airbus A318/A319/A320/A321 ALS Part 2 Revision 02, which
includes also Airbus A319 Corporate Jet, introduces more restrictive
DT ALI maintenance instructions. Failure to comply with these
instructions could result in an unsafe condition.
Application of new DT ALI tasks 531129-02-2 and 531129-02-3
introduces initial and
[[Page 3872]]
repetitive inspections of the windshield central lower node
continuity fittings, replacing the one time inspection for that
subject, previously required by EASA AD 2011-0231 [https://ad.easa.europa.eu/blob/easa_ad_2011_0231.pdf] [associated with FAA
AD 2013-13-03, Amendment 39-17491 (78 FR 41280, July 10, 2013)].
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2010-0071R1 * * *, which are superseded, and
requires compliance with all maintenance tasks as described in
Airbus A318/A319/A320/A321 ALS part 2 at Revision 02.
The unsafe condition is fatigue cracking, accidental damage, or
corrosion in principal structural elements, and possible failure of
certain life limited parts, which could result in reduced structural
integrity of the airplane. You may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-2013-
0002.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the SNPRM (79
FR 30492, May 28, 2014) and the FAA's response to each comment.
Request To Extend Compliance Time
United Airlines (UAL), Delta Airlines (DAL), and Virgin America
asked that we extend the compliance time for incorporation of Airbus
A318/A319/A320/A321 ALS Part 2--Damage-Tolerant Airworthiness
Limitation Items (DT ALI), Revision 02, dated May 28, 2013. UAL stated
that it would like to manage the task incorporation on an individual
basis. UAL proposed that we revise the compliance times specified in
paragraph (n) of the SNPRM (79 FR 30492, May 28, 2014) as follows:
``After the effective date of this AD, incorporate each task into the
program within the specific threshold/interval provided.'' DAL and
Virgin America stated that, to provide time to revise the maintenance
program and perform any related tasks that might exceed the compliance
thresholds specified in the ALI, the grace period specified in
paragraph (n) of the SNPRM should be changed from 4 to 12 months.
DAL asked for more time to update the maintenance program to
incorporate Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28,
2013. DAL and Virgin America requested 9 months, as opposed to 30 days,
because 9 months was the allowed compliance time for incorporating
airworthiness limitation items into the maintenance program required by
AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011).
We acknowledge the commenters' concerns; however, we do not agree
to extend the compliance times for incorporation of the tasks into the
maintenance program. We based the compliance times in this AD primarily
on our assessment of the safety risk. Since some safety issues are more
time-sensitive than others, we consider the overall risk to the fleet,
including the severity of the failure and the likelihood of the
occurrence of the failure. In this case, the primary reason for
requiring incorporation of Airbus A318/A319/A320/A321 ALS Part 2--
Damage-Tolerant Airworthiness Limitation Items (DT ALI), Revision 02,
dated May 28, 2013, is to cover extension of the design service goal
and preliminary results from widespread fatigue damage.
Therefore, we do not agree to extend the grace period or compliance
times for incorporation of the tasks into the maintenance program.
However, under the provisions of paragraph (p)(1) of this AD, we will
consider requests for approval of extending the compliance time based
on the current status of the maintenance and inspection programs
relative to the ALI tasks if sufficient data are submitted to
substantiate that it would provide an acceptable level of safety. We
have not changed this AD in this regard.
``Contacting the Manufacturer'' Paragraph in This AD
Since late 2006, we have included a standard paragraph titled
``Airworthy Product'' in all MCAI ADs in which the FAA develops an AD
based on a foreign authority's AD.
We have become aware that some operators have misunderstood or
misinterpreted the Airworthy Product paragraph to allow the owner/
operator to use messages provided by the manufacturer as approval of
deviations during the accomplishment of an AD-mandated action. The
Airworthy Product paragraph does not approve messages or other
information provided by the manufacturer for deviations to the
requirements of the AD-mandated actions. The Airworthy Product
paragraph only addresses the requirement to contact the manufacturer
for corrective actions for the identified unsafe condition and does not
cover deviations from other AD requirements. However, deviations to AD-
required actions are addressed in 14 CFR 39.17, and anyone may request
the approval for an alternative method of compliance to the AD-required
actions using the procedures found in 14 CFR 39.19.
To address this misunderstanding and misinterpretation of the
Airworthy Product paragraph, we have changed the paragraph and retitled
it ``Contacting the Manufacturer.'' This paragraph now clarifies that
for any requirement in this AD to obtain corrective actions from a
manufacturer, the actions must be accomplished using a method approved
by the FAA, the European Aviation Safety Agency (EASA), or Airbus's
EASA Design Organization Approval (DOA).
The Contacting the Manufacturer paragraph also clarifies that, if
approved by the DOA, the approval must include the DOA-authorized
signature. The DOA signature indicates that the data and information
contained in the document are EASA-approved, which is also FAA-
approved. Messages and other information provided by the manufacturer
that do not contain the DOA-authorized signature approval are not EASA-
approved, unless EASA directly approves the manufacturer's message or
other information.
This clarification does not remove flexibility previously afforded
by the Airworthy Product paragraph. Consistent with long-standing FAA
policy, such flexibility was never intended for required actions. This
is also consistent with the recommendation of the Airworthiness
Directive Implementation Aviation Rulemaking Committee to increase
flexibility in complying with ADs by identifying those actions in
manufacturers' service instructions that are ``Required for
Compliance'' with ADs. We continue to work with manufacturers to
implement this recommendation. But once we determine that an action is
required, any deviation from the requirement must be approved as an
alternative method of compliance.
We also have decided not to include a generic reference to either
the ``delegated agent'' or ``design approval holder (DAH) with State of
Design Authority design organization approval,'' but instead we have
provided the specific delegation approval granted by the State of
Design Authority for the DAH.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
SNPRM (79 FR
[[Page 3873]]
30492, May 28, 2014) for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the SNPRM (79 FR 30492, May 28, 2014).
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Costs of Compliance
We estimate that this AD affects 851 airplanes of U.S. registry.
The actions required by AD 2011-14-06, Amendment 39-16741 (76 FR
42024, July 18, 2011), and retained in this AD take about 1 work-hour
per product, at an average labor rate of $85 per work-hour. Based on
these figures, the estimated cost of the required actions is $85 per
product.
We also estimate that it will take about 1 work-hour per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD on U.S. operators to be $72,335, or $85 per product.
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.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2013-0692; 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 Operations office (telephone 800-647-
5527) is in the ADDRESSES section.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), and adding
the following new AD:
2014-23-15 Airbus: Amendment 39-18031. Docket No. FAA-2013-0692;
Directorate Identifier 2012-NM-024-AD.
(a) Effective Date
This AD becomes effective March 2, 2015.
(b) Affected ADs
This AD replaces AD 2011-14-06, Amendment 39-16741 (76 FR 42024,
July 18, 2011).
(c) Applicability
This AD applies to all Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232,
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 05, Periodic
Inspections.
(e) Reason
This AD was prompted by a determination that more restrictive
limitations are necessary. We are issuing this AD to prevent fatigue
cracking, accidental damage, or corrosion in principal structural
elements, and possible failure of certain life limited parts, 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) Retained Revision of Airworthiness Limitations Section (ALS) To
Incorporate Safe Life Airworthiness Limitation Items (ALIs)
This paragraph restates the requirements of paragraph (g) of AD
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). For
Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114,
-115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -
214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131,
-211, -212, -213, -231, and -232 airplanes: Within 3 months after
November 7, 2007 (the effective date of AD 2007-20-05, Amendment 39-
15215 (72 FR 56262, October 3, 2007)), revise the ALS of the
Instructions for Continued Airworthiness to incorporate Sub-part 1-
2, ``Life Limits,'' and Sub-part 1-3, ``Demonstrated Fatigue
Lives,'' of Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 00, dated February 28,
2006. Accomplish the actions in Sub-part 1-2, ``Life Limits,'' and
Sub-part 1-3, ``Demonstrated Fatigue Lives,'' of Airbus A318/A319/
A320/A321 ALS Part 1--Safe Life Airworthiness Limitation Items,
Revision 00, dated February 28, 2006, at the times specified in Sub-
part 1-2, ``Life Limits,'' and Sub-part 1-3, ``Demonstrated Fatigue
Lives,'' of Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, dated February 28, 2006, except as
provided by paragraph (i) of this AD. Accomplishing the actions
required by paragraph (j) of this AD terminates the requirements of
this paragraph.
(h) Retained Revision to ALS To Incorporate Damage Tolerant ALIs
This paragraph restates certain provisions of paragraph (h) of
AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). For
Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114,
-115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -
214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131,
-211, -212, -213, -231, and -232 airplanes; except Model A319
airplanes on which Airbus Modifications 28238, 28162, and 28342 have
been incorporated in production: Within 14 days after November
[[Page 3874]]
7, 2007 (the effective date of AD 2007-20-05, Amendment 39-15215 (72
FR 56262, October 3, 2007)), revise the ALS of the Instructions for
Continued Airworthiness to incorporate Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue
7, dated December 2005 (approved by the European Aviation Safety
Agency (EASA) on February 7, 2006); Issue 08, dated March 2006
(approved by the EASA on January 4, 2007); or Issue 09, dated
November 2006 (approved by the EASA on May 21, 2007). Accomplish the
actions in Airbus A318/A319/A320/A321 Airworthiness Limitation
Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005;
Issue 08, dated March 2006; or Issue 09, dated November 2006; at the
times specified in Airbus A318/A319/A320/A321 Airworthiness
Limitation Items, Document AI/SE-M4/95A.0252/96, Issue 7, dated
December 2005; Issue 08, dated March 2006; or Issue 09, dated
November 2006; as applicable; except as provided by paragraph (i) of
this AD. Accomplishing the actions required by paragraph (j) or (n)
of this AD, as applicable, terminates the requirements of this
paragraph.
(i) Retained Grace Period for New or More Restrictive Actions
This paragraph restates certain provisions of paragraph (i) of
AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). For
Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114,
-115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -
214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131,
-211, -212, -213, -231, and -232 airplanes: For any new or more
restrictive life-limit introduced with Sub-part 1-2, ``Life
Limits,'' and Sub-part 1-3, ``Demonstrated Fatigue Lives,'' of
Airbus A318/A319/A320/A321 ALS Part 1--Safe Life Airworthiness
Limitation Items, Revision 00, dated February 28, 2006, replace the
part at the time specified in Sub-part 1-2, ``Life Limits,'' and
Sub-part 1-3, ``Demonstrated Fatigue Lives,'' of Airbus A318/A319/
A320/A321 ALS Part 1--Safe Life Airworthiness Limitation Items,
Revision 00, dated February 28, 2006, or within 6 months after
November 7, 2007 (the effective date of AD 2007-20-05, Amendment 39-
15215 (72 FR 56262, October 3, 2007)), whichever is later.
Accomplishing the actions required by paragraph (n) of this AD
terminates the requirements of this paragraph.
(j) Retained Revision of ALS To Incorporate Damage-Tolerant ALIs With
Revised Compliance Times
This paragraph restates the requirements of paragraph (j) of AD
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), with
revised compliance times. Within 9 months after August 22, 2011 (the
effective date of AD 2011-14-06): Revise the maintenance program by
incorporating all maintenance requirements and associated
airworthiness limitations specified in the Airbus A318/A319/A320/
A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96,
Issue 10, dated October 2009; or Issue 11, dated September 2010.
Comply with all applicable maintenance requirements and associated
airworthiness limitations included in Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue
10, dated October 2009; or Issue 11, dated September 2010; except as
provided by paragraph (k) of this AD. Accomplishing the actions
required by this paragraph terminates the requirements of paragraph
(h) of this AD. Accomplishing the actions required by paragraph (n)
of this AD terminates the requirements of this paragraph.
(k) Retained Special Compliance Times for Certain Tasks
This paragraph restates the requirements of paragraph (k) of AD
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), with
changes to table 1 to paragraph (k) of this AD. For new and more
restrictive tasks introduced with Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue
10, dated October 2009; or Issue 11, dated September 2010; as
specified in table 1 to paragraph (k) of this AD: The initial
compliance time for doing the tasks is specified in table 1 to
paragraph (k) of this AD. Accomplishing the actions required by
paragraph (n) of this AD terminates the requirements of this
paragraph.
Table 1 to Paragraph (k) of This AD--Compliance Times for Tasks
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Task Applicability............ Compliance time, whichever occurs later
(as specified in the
applicability column of
the task).
----------------------------------------------------------------------------------------------------------------
545102-01-6...................... Group 19-1A CFM, Group 19- The threshold as defined Within 2,000 flight
1B CFM, and Model in Airbus A318/A319/ cycles or 5,500 flight
A320[dash]200 airplanes A320/A321 Airworthiness hours, after August 22,
with CFM Industrial Limitation Items, 2011 (the effective
(CFM)/International Aero Document AI/SE[dash]M4/ date of AD 2011-14-06,
Engine (IAE) engines. 95A.0252/96, Issue 10, Amendment 39-16741 (76
dated October 2009; or FR 42024, July 18,
Issue 11, dated 2011)), whichever
September 2010. occurs first.
545102-01-7...................... Model A320-100 series The threshold as defined Within 2,000 flight
airplanes. in Airbus A318/A319/ cycles or 2,000 flight
A320/A321 Airworthiness hours, after August 22,
Limitation Items, 2011 (the effective
Document AI/SE[dash]M4/ date of AD 2011-14-06,
95A.0252/96, Issue 10, Amendment 39-16741 (76
dated October 2009; or FR 42024, July 18,
Issue 11, dated 2011)), whichever
September 2010. occurs first.
572050-01-1 or alternative task Group 19[dash]1A and At the time of the next Within 6 months after
572050[dash]02-1. Group 19-1B airplanes. due accomplishment of August 22, 2011 (the
any one of the tasks effective date of AD
572004, 572020, or 2011-14-06, Amendment
572053 as currently 39-16741 (76 FR 42024,
described in the Airbus July 18, 2011)).
A318/A319/A320/A321
Airworthiness
Limitation Items,
Document AI/SE[dash]M4/
95A.0252/96, Issue 7,
dated December 2005;
Issue 08, dated March
2006; or Issue 09,
dated November 2006.
572050-01-4 or alternative task Model A320-200 series At the time of the next Within 6 months after
572050[dash]02-4. airplanes. due accomplishment of August 22, 2011 (the
any one of the tasks effective date of AD
572004, 572020, or 2011-14-06, Amendment
572053 as currently 39-16741 (76 FR 42024,
described in the Airbus July 18, 2011)).
A318/A319/A320/A321
Airworthiness
Limitation Items,
Document AI/SE[dash]M4/
95A.0252/96, Issue 7,
dated December 2005;
Issue 08, dated March
2006; or Issue 09,
dated November 2006.
[[Page 3875]]
572050-01-5 or alternative task Group 21[dash]1A At the time of the next Within 6 months after
572050[dash]02-5. airplanes. due accomplishment of August 22, 2011 (the
any one of the tasks effective date of AD
572004, 572020, or 2011-14-06, Amendment
572053 as currently 39-16741 (76 FR 42024,
described in the Airbus July 18, 2011)).
A318/A319/A320/A321
Airworthiness
Limitation Items,
Document AI/SE[dash]M4/
95A.0252/96, Issue 7,
dated December 2005;
Issue 08, dated March
2006; or Issue 09,
dated November 2006.
572050-01-7 or alternative task Model A320-100 series At the time of the next Within 6 months after
572050[dash]02-7. airplanes. due accomplishment of August 22, 2011 (the
any one of the tasks effective date of AD
572004, 572020, or 2011-14-06, Amendment
572053 as currently 39-16741 (76 FR 42024,
described in the Airbus July 18, 2011)).
A318/A319/A320/A321
Airworthiness
Limitation Items,
Document AI/SE[dash]M4/
95A.0252/96, Issue 7,
dated December 2005;
Issue 08, dated March
2006; or Issue 09,
dated November 2006.
534132-01-1...................... Model A320 PRE 30748 The threshold/interval Within 100 days after
airplanes. as defined in Airbus August 22, 2011 (the
A318/A319/A320/A321 effective date of AD
Airworthiness 2011-14-06, Amendment
Limitation Items, 39-16741 (76 FR 42024,
Document AI/SE[dash]M4/ July 18, 2011)),
95A.0252/96, Issue 10, without exceeding the
dated October 2009; or previous threshold/
Issue 11, dated interval as defined in
September 2010. Airbus A318/A319/A320/
A321 Airworthiness
Limitation Items,
Document AI/SE[dash]M4/
95A.0252/96, Issue 7,
dated December 2005;
Issue 08, dated March
2006; or Issue 09,
dated November 2006.
531118-01-1...................... Model A318 (except (A318- The threshold/interval Within 100 days after
121 and [dash]122), as defined in Airbus August 22, 2011 (the
Group 19-1A, Group 19- A318/A319/A320/A321 effective date of AD
1B, and Model A320 and Airworthiness 2011-14-06, Amendment
A321 series airplanes. Limitation Items, 39-16741 (76 FR 42024,
Document AI/SE[dash]M4/ July 18, 2011)),
95A.0252/96, Issue 10, without exceeding the
dated October 2009; or previous threshold/
Issue 11, dated interval as defined in
September 2010. Airbus A318/A319/A320/
A321 Airworthiness
Limitation Items,
Document AI/SE[dash]M4/
95A.0252/96, Issue 7,
dated December 2005;
Issue 08, dated March
2006; or Issue 09,
dated November 2006.
531118-01-1...................... Model A318-121 and The threshold/interval Within 100 days after
[dash]122 airplanes. as defined in Airbus August 22, 2011 (the
A318/A319/A320/A321 effective date of AD
Airworthiness 2011-14-06, Amendment
Limitation Items, 39-16741 (76 FR 42024,
Document AI/SE[dash]M4/ July 18, 2011)).
95A.0252/96, Issue 10,
dated October 2009; or
Issue 11, dated
September 2010.
----------------------------------------------------------------------------------------------------------------
Note 1 to table 1 to paragraph (k) of this AD: ALI Task 572050
refers to the outer wing dry bay and is comprised of extracts from
three ALI Tasks 572004, 572020, and 572053. The threshold of ALI
Task 572050 for the whole dry bay area is that of the lowest
threshold of the source ALI tasks, i.e., that of ALI Task 572053.
(l) Retained Limitation: No Alternative Life Limits, Inspections, or
Inspection Intervals After Accomplishment of the Actions Specified in
Paragraphs (g) and (h) of This AD
This paragraph restates the requirements of paragraph (l) of AD
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). After
the actions specified in paragraphs (g) and (h) of this AD have been
accomplished, no alternative life limits, inspections, or inspection
intervals may be used, except as provided by paragraphs (i) and (m)
of this AD, and except as required by paragraphs (j) and (n) of this
AD.
(m) Retained Limitation: No Alternative Life Limits, Inspections, or
Inspection Intervals After Accomplishment of the Actions Specified in
Paragraph (j) of This AD
This paragraph restates the requirements of paragraph (m) of AD
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). After
the actions specified in paragraph (j) of this AD have been
accomplished, no alternative life limits, inspections, or inspection
intervals may be used, except as required by paragraph (n) of this
AD.
(n) New Maintenance or Inspection Program Revision
Within 30 days after the effective date of this AD, revise the
maintenance or inspection program, as applicable, to incorporate the
ALIs specified in paragraphs (n)(1), (n)(2), and (n)(3) of this AD.
The initial compliance time for accomplishing the actions is at the
applicable time specified in the ALIs specified in paragraphs
(n)(1), (n)(2), and (n)(3) of this AD; or within 4 months after the
effective date of this AD; whichever occurs
[[Page 3876]]
later. Accomplishing these actions terminates the requirements of
paragraphs (g), (h), (i), (j), and (k) of this AD.
(1) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 02, dated May 13, 2011.
(2) Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28,
2013.
(3) Airbus A318/A319/A320/A321 ALS Part 4--Ageing Systems
Maintenance, dated January 8, 2008.
(o) New Limitation: No Alternative Actions, Intervals, and/or Critical
Design Configuration Control Limitations (CDCCLs)
After accomplishing the revision required by paragraph (n) of
this AD, no alternative actions (e.g., inspections), intervals, and/
or CDCCLs may be used unless the actions, intervals, and/or CDCCLs
are approved as an alternative method of compliance (AMOC) in
accordance with the procedures specified in paragraph (p)(1) of this
AD.
(p) 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.
(i) 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. The AMOC approval letter must specifically
reference this AD.
(ii) AMOCs approved previously for AD 2011-14-06, Amendment 39-
16741 (76 FR 42024, July 18, 2011), are approved as AMOCs for the
corresponding actions specified in this AD.
(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 Branch, ANM-116, Transport
Airplane Directorate, 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.
(q) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
European Aviation Safety Agency Airworthiness Directives 2012-0008,
dated January 16, 2012; and 2013-0147, dated July 16, 2013; for
related information. You may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov/#!documentDetail;D=FAA-
2013-0692-0002.
(r) 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 A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 02, dated May 13, 2011. The
revision level of this document is identified on only the title page
and in the Record of Revisions. The revision date is not identified
on the title page of this document.
(ii) Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28,
2013. The revision date of this document is not identified on the
title page of this document.
(iii) Airbus A318/A319/A320/A321 ALS Part 4--Ageing Systems
Maintenance, dated January 8, 2008. The revision date of this
document is not identified on the title page of this document.
(3) The following service information was approved for IBR on
August 22, 2011 (76 FR 42024, July 18, 2011).
(i) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009. The
revision level of this document is identified on only the title page
and in the Record of Revisions.
(ii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 11, dated September 2010. The
revision level of this document is identified on only the title page
and in the Record of Revisions.
(4) The following service information was approved for IBR on
November 7, 2007 (72 FR 56262, October 3, 2007).
(i) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 00, dated February 28,
2006.
(ii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005
(approved by the European Aviation Safety Agency (EASA) on February
7, 2006).
Note 2 to paragraph (r)(4)(ii) of this AD: This document
contains the following errors: The Summary of Changes is comprised
of 11 pages, which are all identified as Page 2--LEP of Section LEP
instead of Page 1--SOC [through] Page 11--SOC of Section SOC; the
List of Effective Pages only refers to Page 1--SOC for the Summary
of Changes. The List of Effective Pages is comprised of two pages,
and both of those pages are identified as Page 2--LEP. The first
page of Section 2 is identified as Page 6 of Section 1 and is not
referred to in the List of Effective Pages.
(iii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 08, dated March 2006 (approved
by the EASA on January 4, 2007).
(iv) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 09, dated November 2006
(approved by the EASA on May 21, 2007).
(5) 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.
(6) 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.
(7) 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 December 23, 2014.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-01257 Filed 1-23-15; 8:45 am]
BILLING CODE 4910-13-P
