[Federal Register Volume 79, Number 102 (Wednesday, May 28, 2014)]
[Proposed Rules]
[Pages 30492-30498]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-12251]


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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: Supplemental notice of proposed rulemaking (NPRM); reopening of 
comment period.

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SUMMARY: We are revising an earlier proposed airworthiness directive 
(AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. 
The NPRM proposed to supersede AD 2011-14-06 and proposed revising the 
maintenance program. The NPRM was prompted by the determination that 
more restrictive limitations are necessary. This action revises the 
NPRM by 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. Since these actions 
impose an additional burden over that proposed in the NPRM, we are 
reopening the comment period to allow the public the chance to comment 
on these proposed changes.

DATES: We must receive comments on this proposed AD by July 14, 2014.

[[Page 30493]]


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 [email protected]; 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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; 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 proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket 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

    We proposed to amend 14 CFR part 39 with an earlier NPRM for the 
specified products, which was published in the Federal Register on 
August 13, 2013 (78 FR 49213). The NPRM proposed to supersede AD 2011-
14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), to require 
actions intended to address the unsafe condition for Airbus Model A318, 
A319, A320, and A321 series airplanes.
    Since the NPRM (78 FR 49213, August 13, 2013) was issued, it has 
been determined that more restrictive limits are needed for damage 
tolerant airworthiness limitation items. This supplemental notice of 
proposed rulemaking (SNPRM) would require revising the maintenance 
program to incorporate new limitations.
    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 the specified 
products. 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 by searching for and 
locating it in Docket No. FAA-2013-0692.

Relevant Service Information

    Airbus has issued A318/A319/A320/A321 ALS Part 2--Damage-Tolerant 
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28, 
2013. The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

Comments

    We gave the public the opportunity to comment on the NPRM (78 FR 
49213, August 13, 2013). The following presents the comments received 
on the NPRM and the FAA's response to each comment.

Request To Incorporate Airbus A318/A319/A320/A321 ALS Part 2, Revision 
02, Dated May 28, 2013, in Paragraph (m) of the NPRM (78 FR 49213, 
August 13, 2013)

    American Airlines (AAL) requested that we either delete the phrase 
``doing the actions required by paragraph (m) of this AD terminates the 
requirements of this paragraph,'' from paragraph (i) of the NPRM (78 FR 
49213, August 13, 2013), or incorporate Airbus A318/A319/A320/A321 ALS 
Part 2--Damage-Tolerant Airworthiness Limitation Items (DT ALI), 
Revision 02, dated May 28, 2013, in paragraph (m) of the NPRM. The 
commenter stated that paragraph (m) of the NPRM does not require 
incorporation of Airbus A318/A319/A320/A321 ALS Part 2, Revision 02, 
dated May 28, 2013; therefore, incorporating paragraph (m) would not

[[Page 30494]]

fully terminate requirements of paragraph (i) of the NPRM.
    We agree to revise the final rule by adding the incorporation of 
Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant Airworthiness 
Limitation Items (DT ALI), Revision 02, dated May 28, 2013, to 
paragraph (p) of this SNPRM.

Request To Incorporate Airbus A318/A319/A320/A321 ALS Part 3--
Certification Maintenance Requirements (CMR), Revision 01, Dated June 
15, 2012; in Paragraph (m) of the NPRM (78 FR 49213, August 13, 2013)

    AAL requested that we incorporate Airbus ALS Part 3--CMR, Revision 
01, dated June 15, 2012; in paragraph (m) of the NPRM (78 FR 49213, 
August 13, 2013).
    We acknowledge that the latest approved CMR has been released; 
however, we disagree to revise this SNPRM. EASA has issued a separate 
AD 2013-0148, dated July 16, 2013 to require Airbus ALS Part 3--CMR, 
Revision 01, dated June 15, 2012. Therefore, we are considering 
separate rulemaking for mandating Airbus ALS Part 3--CMR, Revision 01, 
dated June 15, 2012. No change has been made to this SNPRM in this 
regard.

Request To Incorporate Airbus A318/A319/A320/A321 ALS Part 4--Ageing 
Systems Maintenance (ASM), Revision 01, Dated June 15, 2012 in 
Paragraph (m) of the NPRM (78 FR 49213, August 13, 2013)

    Airbus and AAL requested that we revise paragraph (m) of the NPRM 
(78 FR 49213, August 13, 2013) to incorporate Airbus A318/A319/A320/
A321 ALS Part 4--ASM, Revision 01, dated June 15, 2012. Airbus stated 
that the NPRM mentions Airbus A318/A319/A320/A321 ALS Part 4--ASM, 
dated January 8, 2008; however, Airbus A318/A319/A320/A321 ALS Part 4--
ASM, Revision 01, dated June 15, 2012, introduces the extended service 
goal 1 (ESG1) exercise which allows continued operation of the A320-200 
systems post-modification 39020 at a different compliance time.
    We acknowledge that the latest approved ALS Part 4 has been 
released; however, we disagree to revise this SNPRM. EASA has issued 
EASA AD 2013-0146, dated July 16, 2013 to require Airbus A318/A319/
A320/A321 ALS Part 4--ASM, Revision 01, dated June 15, 2012. Therefore, 
we might consider separate rulemaking for mandating Airbus A318/A319/
A320/A321 ALS Part 4--ASM, Revision 01, dated June 15, 2012. No change 
has been made to this SNPRM in this regard.

Retained Paragraph of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, 
July 18, 2011)

    The NPRM (78 FR 49213, August 13, 2013) did not retain paragraph 
(h) of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). 
We have retained that paragraph as paragraph (h) of this SNPRM and have 
re-designated the subsequent paragraphs accordingly.

Differences Between This Proposed AD and the MCAI or Service 
Information

    The MCAI specifies that if there are findings from the ALS 
inspection tasks, corrective actions must be accomplished in accordance 
with Airbus maintenance documentation. However, this proposed AD does 
not include that requirement. Operators of U.S.-registered airplanes 
are required by general airworthiness and operational regulations to 
perform maintenance using methods that are acceptable to the FAA. We 
consider those methods to be adequate to address any corrective actions 
necessitated by the findings of ALS inspections required by this 
proposed AD.

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 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.
    Certain changes described above expand the scope of the NPRM (78 FR 
49213, August 13, 2013). As a result, we have determined that it is 
necessary to reopen the comment period to provide additional 
opportunity for the public to comment on this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 851 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD.
    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 required 
actions is $85 per product.
    We also estimate that it would take about 1 work-hour per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this 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 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.

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,

[[Page 30495]]

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. Amend Sec.  39.13 by removing Airworthiness Directive (AD) 2011-14-
06, Amendment 39-16741 (76 FR 42024, July 18, 2011) and by 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 July 14, 2014.

(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

    Comply with this AD within the compliance times specified, 
unless already 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 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 (i) of this 
AD. Doing the actions required by paragraph (n) 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 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. Doing the actions required by 
paragraph (j) of this AD terminates the requirements of this 
paragraph. Doing the actions required by paragraph (n) of this AD 
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, 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. 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. Doing 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 specified in 
paragraph (n) of this AD terminates the requirements of this 
paragraph.

[[Page 30496]]



                        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   The threshold as         Within 2,000 flight
                                        19-1B CFM, and Model     defined in Airbus A318/  cycles or 5,500 flight
                                        A320-200 airplanes       A319/A320/A321           hours, after August
                                        with CFM Industrial      Airworthiness            22, 2011 (the
                                        (CFM)/International      Limitation Items,        effective date of AD
                                        Aero Engine (IAE)        Document AI/SE-M4/       2011-14-06, Amendment
                                        engines.                 95A.0252/96, Issue 10,   39-16741 (76 FR 42024,
                                                                 dated October 2009; or   July 18, 2011)),
                                                                 Issue 11, dated          whichever occurs
                                                                 September 2010.          first.
545102-01-7..........................  Model A320-100 series    The threshold as         Within 2,000 flight
                                        airplanes.               defined in Airbus A318/  cycles or 2,000 flight
                                                                 A319/A320/A321           hours, after August
                                                                 Airworthiness            22, 2011 (the
                                                                 Limitation Items,        effective date of AD
                                                                 Document AI/SE-M4/       2011-14-06, Amendment
                                                                 95A.0252/96, Issue 10,   39-16741 (76 FR 42024,
                                                                 dated October 2009; or   July 18, 2011)),
                                                                 Issue 11, dated          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
                                                                 572053 as currently      39-16741 (76 FR 42024,
                                                                 described in the         July 18, 2011)).
                                                                 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.
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
                                                                 572053 as currently      39-16741 (76 FR 42024,
                                                                 described in the         July 18, 2011)).
                                                                 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.
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
                                                                 572053 as currently      39-16741 (76 FR 42024,
                                                                 described in the         July 18, 2011)).
                                                                 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.


[[Page 30497]]


                   Table 1--To Paragraph (k) of This AD--Compliance Times for Tasks--Continued
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
Task                                   Applicability..........       Compliance time, whichever occurs later
                                       (as specified in.......
                                       the applicability......
                                       column of the task)....
----------------------------------------------------------------------------------------------------------------
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
                                                                 572053 as currently      39-16741 (76 FR 42024,
                                                                 described in the         July 18, 2011)).
                                                                 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.
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-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-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   Within 100 days after
                                        (A318-121 and -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-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-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 -122  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-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.

[[Page 30498]]

(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 
Airworthiness Limitation Items specified in paragraphs (n)(1), 
(n)(2), and (n)(3) of this AD. The initial compliance time for the 
accomplishing the actions is at the applicable time specified in 
Airworthiness Limitation Items 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. Doing 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: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD. 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) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or the DAH with a State of Design Authority's 
design organization approval). You are required to ensure the 
product is airworthy before it is returned to service.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2012-0008, dated January 16, 
2012; and 2013-0147, dated July 16, 2013; for related information. 
This MCAI may be found in the AD docket on the Internet at http://www.regulations.gov by searching for and locating it in Docket No. 
FAA-2013-0692.
    (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 [email protected]; 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.

    Issued in Renton, Washington, on May 15, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-12251 Filed 5-27-14; 8:45 am]
BILLING CODE 4910-13-P