[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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