
[Federal Register Volume 78, Number 156 (Tuesday, August 13, 2013)]
[Proposed Rules]
[Pages 49213-49217]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-19528]


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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]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede airworthiness directive (AD) 2011-14-
06 that applies to all Airbus Model A318, A319, A320, and A321 series 
airplanes. That AD currently requires revising the maintenance program. 
Since we issued that AD, we have determined that more restrictive 
limitations are necessary. This proposed AD would require revising the 
maintenance program to incorporate new limitations. We are proposing 
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: We must receive comments on this proposed AD by September 27, 
2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed 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 http://www.airbus.com. You may review copies of the 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed 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. Comments will be available in the AD docket 
shortly after receipt.

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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0692; 
Directorate Identifier 2012-NM-024-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On June 24, 2011, we issued AD 2011-14-06, Amendment 39-16741 (76 
FR 42024, July 18, 2011). That AD required actions intended to address 
an unsafe condition on the products listed above.
    Since we issued AD 2011-14-06, Amendment 39-16741 (76 FR 42024, 
July 18, 2011), we have determined that more restrictive limitations 
are necessary. The European Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Community, has 
issued EASA Airworthiness Directive 2012-0008, dated January 16, 2012 
(referred to after this as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

The airworthiness limitations for Airbus aeroplanes are currently 
published in Airworthiness Limitations Section (ALS) documents. The 
airworthiness limitations applicable to the Safe Life Airworthiness 
Limitation Items (SL ALI) are specified in Airbus A318/A319/A320/
A321 ALS Part 1, which is approved by the European Aviation Safety 
Agency (EASA).
EASA AD 2006-0162 [which corresponds to FAA AD 2007-20-05, Amendment 
39-15215 (72 FR 56262, October 3, 2007) which was superseded by FAA 
AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011)] was 
issued to require the implementation of the instructions and 
airworthiness limitations as specified in Airbus A318/A319/A320/A321 
ALS Part 1 original issue. Failure to comply with the instructions 
of ALS Part 1 could result in an unsafe condition.
This [EASA] AD retains the requirements of EASA AD 2006-0162, which 
is superseded, extends the applicability by adding the Models A318-
121, A318-122, A320-215 and A320-216, and requires the 
implementation of the instructions and airworthiness limitations as 
specified in Airbus A318/A319/A320/A321 ALS part 1 revision 02, 
approved on 13 May 2011.

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. The required actions also include revising 
the maintenance program to include Airbus A318/A319/A320/A321 ALS Part 
4--Ageing Systems Maintenance, dated January 8, 2008. You may obtain 
further information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation Items, Revision 02, dated May 13, 2011; and 
A318/A319/A320/A321 ALS Part 4--Ageing Systems Maintenance, dated 
January 8, 2008. The actions described in this service information are 
intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation

[[Page 49214]]

in the United States. Pursuant to our bilateral agreement with the 
State of Design Authority, we have been notified of the unsafe 
condition described in the MCAI and service information referenced 
above. We are proposing this AD because we evaluated all pertinent 
information and determined an unsafe condition exists and is likely to 
exist or develop on other products of the same type design.
    This proposed AD requires revisions to certain operator maintenance 
documents to include new actions. Compliance with these actions is 
required by section 91.403(c) of the Federal Aviation Regulations (14 
CFR 91.403(c)). For airplanes that have been previously modified, 
altered, or repaired in the areas addressed by these inspections, an 
operator might not be able to accomplish the actions described in the 
revisions. In this situation, to comply with 14 CFR 91.403(c), the 
operator must request approval of an alternative method of compliance 
(AMOC) in accordance with the provisions of paragraph (o) of this 
proposed AD. The request should include a description of changes to the 
required inspections that will ensure the continued damage tolerance of 
the affected structure and the continued operational safety of the 
airplane.

Differences Between This AD and the MCAI or Service Information

    Although the MCAI requires revising the maintenance program to 
include the incorporation of Airbus A318/A319/A320/A321 ALS Part 1--
Safe Life Airworthiness Limitation Items, Revision 02, dated May 13, 
2011, this AD also requires revising the maintenance program to include 
the incorporation of Airbus A318/A319/A320/A321 ALS Part 4--Ageing 
Systems Maintenance, dated January 8, 2008. This difference has been 
coordinated with EASA.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 851 products of U.S. registry.
    The actions that are required by AD 2011-14-06, Amendment 39-16741 
(76 FR 42024, July 18, 2011), and retained in this proposed 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 currently 
required actions is $85 per product.
    We estimate that it would take about 1 work-hour per product to 
comply with the new basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of the proposed 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 proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

Airbus: Docket No. FAA-2013-0692; Directorate Identifier 2012-NM-
024-AD.

(a) Comments Due Date

    We must receive comments by September 27, 2013.

(b) Affected ADs

    This AD supersedes 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; certificated in any category.

(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

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Revision of Airworthiness Limitations Section (ALS) To 
Incorporate Safe Life 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

[[Page 49215]]

ALS Part 1--Safe Life Airworthiness Limitation Items, 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, 
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 (h) of this AD. Doing the actions required by paragraph 
(m) of this AD terminates the requirements of this paragraph.

(h) 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, 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, 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.

(i) 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 (j) of this AD. Doing the actions required by 
paragraph (m) of this AD terminates the requirements of this 
paragraph.

(j) 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 (j) 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 (j) of this AD: The initial 
compliance time for doing the tasks is specified in table 1 to 
paragraph (j) of this AD.

                         Table 1 to Paragraph (j) of This AD--Compliance Times for Tasks
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
Task                                   Applicability (as           Compliance time, whichever occurs later
                                        specified in the
                                      applicability column
                                          of the task)
----------------------------------------------------------------------------------------------------------------
545102-01-6.......................  Group 19-1A CFM, Group  The threshold as defined   Within 2,000 flight
                                     19-1B CFM, and Model    in Airbus A318/A319/A320/  cycles or 5,500 flight
                                     A320-200 airplanes      A321 Airworthiness         hours, after August 22,
                                     with CFM Industrial     Limitation Items,          2011 (the effective date
                                     (CFM)/International     Document AI/SE-M4/         of AD 2011-14-06,
                                     Aero Engine (IAE)       95A.0252/96, Issue 10,     Amendment 39-16741 (76
                                     engines.                dated October 2009; or     FR 42024, July 18,
                                                             Issue 11, dated            2011)), whichever occurs
                                                             September 2010.            first.
545102-01-7.......................  Model A320-100 series   The threshold as defined   Within 2,000 flight
                                     airplanes.              in Airbus A318/A319/A320/  cycles or 2,000 flight
                                                             A321 Airworthiness         hours, after August 22,
                                                             Limitation Items,          2011 (the effective date
                                                             Document AI/SE-M4/         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 occurs
                                                             September 2010.            first.
572050-01-1 or alternative task     Group 19-1A and Group   At the time of the next    Within 6 months after
 572050-02-1.                        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 39-
                                                             572053 as currently        16741 (76 FR 42024, July
                                                             described in the Airbus    18, 2011)).
                                                             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.
572050-01-4 or alternative task     Model A320-200 series   At the time of the next    Within 6 months after
 572050-02-4.                        airplanes.              due accomplishment of      August 22, 2011 (the
                                                             any one of the tasks       effective date of AD
                                                             572004, 572020, or         2011-14-06, Amendment 39-
                                                             572053 as currently        16741 (76 FR 42024, July
                                                             described in the Airbus    18, 2011)).
                                                             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.

[[Page 49216]]

 
572050-01-5 or alternative task     Group 21-1A airplanes.  At the time of the next    Within 6 months after
 572050-02-5.                                                due accomplishment of      August 22, 2011 (the
                                                             any one of the tasks       effective date of AD
                                                             572004, 572020, or         2011-14-06, Amendment 39-
                                                             572053 as currently        16741 (76 FR 42024, July
                                                             described in the Airbus    18, 2011)).
                                                             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.
572050-01-7 or alternative task     Model A320-100 series   At the time of the next    Within 6 months after
 572050-02-7.                        airplanes.              due accomplishment of      August 22, 2011 (the
                                                             any one of the tasks       effective date of AD
                                                             572004, 572020, or         2011-14-06, Amendment 39-
                                                             572053 as currently        16741 (76 FR 42024, July
                                                             described in the Airbus    18, 2011)).
                                                             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.
534132-01-1.......................  Model A320 PRE 30748    The threshold/interval as  Within 100 days after
                                     airplanes.              defined in Airbus A318/    August 22, 2011 (the
                                                             A319/A320/A321             effective date of AD
                                                             Airworthiness Limitation   2011-14-06, Amendment 39-
                                                             Items, Document AI/SE-M4/  16741 (76 FR 42024, July
                                                             95A.0252/96, Issue 10,     18, 2011)), without
                                                             dated October 2009; or     exceeding the previous
                                                             Issue 11, dated            threshold/interval as
                                                             September 2010.            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.
531118-01-1.......................  Model A318 (except      The threshold/interval as  Within 100 days after
                                     (A318-121 and -122),    defined in Airbus A318/    August 22, 2011 (the
                                     Group 19-1A, Group 19-  A319/A320/A321             effective date of AD
                                     1B, and Model A320      Airworthiness Limitation   2011-14-06, Amendment 39-
                                     and A321 series         Items, Document AI/SE-M4/  16741 (76 FR 42024, July
                                     airplanes.              95A.0252/96, Issue 10,     18, 2011)), without
                                                             dated October 2009; or     exceeding the previous
                                                             Issue 11, dated            threshold/interval as
                                                             September 2010.            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.
531118-01-1.......................  Model A318-121 and -    The threshold/interval as  Within 100 days after
                                     122 airplanes.          defined in Airbus A318/    August 22, 2011 (the
                                                             A319/A320/A321             effective date of AD
                                                             Airworthiness Limitation   2011-14-06, Amendment 39-
                                                             Items, Document AI/SE-M4/  16741 (76 FR 42024, July
                                                             95A.0252/96, Issue 10,     18, 2011)).
                                                             dated October 2009; or
                                                             Issue 11, dated
                                                             September 2010.
----------------------------------------------------------------------------------------------------------------
Note 1 to table 1 to paragraph (j) 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.

(k) Retained Limitation: No Alternative Life Limits, Inspections, or 
Inspection Intervals After Accomplishment of the Actions Specified in 
Paragraph (g) 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 paragraph (g) of this AD have been 
accomplished, no alternative life limits, inspections, or inspection 
intervals may be used, except as provided by paragraph (h) of this 
AD, and except as required by paragraph (m) of this AD.

(l) 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 (i) of this AD have been 
accomplished, no alternative life limits, inspections, or inspection 
intervals may be used, except as required by paragraph (m) of this 
AD.

(m) New Maintenance Program Revision

    Within 30 days after the effective date of this AD, revise the 
maintenance program to incorporate Airbus A318/A319/A320/A321 ALS 
Part 1--Safe Life Airworthiness Limitation Items, Revision 02, dated 
May 13, 2011; and Airbus A318/A319/A320/A321 ALS Part 4--Ageing 
Systems Maintenance, dated January 8, 2008. The initial compliance 
time for the accomplishing the actions is at the applicable time 
specified in Airbus A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation Items, Revision 02, dated May 13, 2011, and 
Airbus A318/A319/A320/A321 ALS Part 4--Ageing Systems

[[Page 49217]]

Maintenance, dated January 8, 2008; or within 4 months after the 
effective date of this AD; whichever occurs later.

(n) New Limitation: No Alternative Actions or Intervals

    After accomplishing the revision required by paragraph (m) of 
this AD, no alternative actions (e.g., inspections) or intervals, 
may be used unless the actions or intervals are approved as an 
alternative method of compliance (AMOC) in accordance with the 
procedures specified in paragraph (o) of this AD.

(o) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the International 
Branch, send it to ATTN: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your 
appropriate principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must 
specifically reference this AD. AMOCs approved previously in 
accordance with 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
European Aviation Safety Agency (EASA) Airworthiness Directive 2012-
0008, dated January 16, 2012, and the service information specified 
in paragraphs (p)(1)(i) through (p)(1)(viii) of this AD, for related 
information.
    (i) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation Items, Revision 02, dated May 13, 2011.
    (ii) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life 
Airworthiness Limitation Items, dated February 28, 2006.
    (iii) Airbus A318/A319/A320/A321 ALS Part 4--Ageing Systems 
Maintenance, dated January 8, 2008.
    (iv) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, 
Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005.
    (v) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, 
Document AI/SE-M4/95A.0252/96, Issue 08, dated March 2006.
    (vi) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, 
Document AI/SE-M4/95A.0252/96, Issue 09, dated November 2006.
    (vii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items, 
Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009.
    (viii) Airbus A318/A319/A320/A321 Airworthiness Limitation 
Items, Document AI/SE-M4/95A.0252/96, Issue 11, dated September 
2010.
    (2) 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 http://www.airbus.com. You may review copies of the 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.

    Issued in Renton, Washington, on August 2, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2013-19528 Filed 8-12-13; 8:45 am]
BILLING CODE 4910-13-P


