[Federal Register Volume 80, Number 16 (Monday, January 26, 2015)]
[Rules and Regulations]
[Pages 3871-3876]
[FR Doc No: 2015-01257]

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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

AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).

ACTION: Final rule.

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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 http://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<EMAIL_ADDRESS>Internet http://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<PHONE_NUMBER>;
fax<PHONE_NUMBER>.

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 [http://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

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 [http://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 http://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

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 http://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

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.

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

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<PHONE_NUMBER>; fax<PHONE_NUMBER>. Information may be
emailed to<EMAIL_ADDRESS>    (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 http://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<EMAIL_ADDRESS>Internet http://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<PHONE_NUMBER>, or go to: http://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