AD 2015-05-02
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus | A318 | Airworthiness Directives; Airbus Airplanes |
Unsafe Condition
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.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Revise the maintenance or inspection program to incorporate the airworthiness limitations specified in paragraphs (n)(1) and (n)(2) of this AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Before further flight
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
All Airbus Model A318, A319, A320, and A321 series airplanes.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
We are superseding Airworthiness Directive (AD) 2014-23-15 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014- 23-15 required revising the maintenance or inspection program to incorporate new, more restrictive airworthiness limitations. This new AD retains the requirement to revise the maintenance or inspection program and removes a conflicting requirement. This AD was prompted by a determination that certain limitations required by AD 2014-23-15 conflict with limitations required by another AD. 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.
Applicability Source Text
Show captured applicability text from the source AD
(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.
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 80, Number 55 (Monday, March 23, 2015)]
[Rules and Regulations]
[Pages 15152-15157]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2015-05731]
[[Page 15152]]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-0489; Directorate Identifier 2015-NM-013-AD;
Amendment 39-18112; AD 2015-05-02]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2014-23-15 for
all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014-
23-15 required revising the maintenance or inspection program to
incorporate new, more restrictive airworthiness limitations. This new
AD retains the requirement to revise the maintenance or inspection
program and removes a conflicting requirement. This AD was prompted by
a determination that certain limitations required by AD 2014-23-15
conflict with limitations required by another AD. We are issuing this
AD to prevent fatigue cracking, accidental damage, or corrosion in
principal structural elements, and possible failure of certain life
limited parts, which could result in reduced structural integrity of
the airplane.
DATES: This AD becomes effective March 23, 2015.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of March 2, 2015
(80 FR 3871, January 26, 2015).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of August
22, 2011 (76 FR 42024, July 18, 2011).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
November 7, 2007 (72 FR 56262, October 3, 2007).
We must receive comments on this AD by May 7, 2015.
ADDRESSES: You may send comments by any of the following methods:
<bullet> Federal eRulemaking Portal: Go to <a href="http://www.regulations.gov">http://www.regulations.gov</a>. Follow the instructions for submitting comments.
<bullet> Fax: 202-493-2251.
<bullet> 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.
<bullet> 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 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 <a href="/cdn-cgi/l/email-protection#325351515d475c461c535b40455d40465a1f57534172535b405047411c515d5f"><span class="__cf_email__" data-cfemail="5d3c3e3e32283329733c342f2a322f293570383c2e1d3c342f3f282e733e3230">[email protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2015-
0489; 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 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:
Discussion
On December 23, 2014, we issued AD 2014-23-15, Amendment 39-18031
(80 FR 3871, January 26, 2015), to supersede AD 2011-14-06, Amendment
39-16741 (76 FR 42024, July 18, 2011). AD 2014-23-15 applied to all
Airbus Model A318, A319, A320, and A321 series airplanes. AD 2014-23-15
was prompted by the determination that more restrictive airworthiness
limitations were necessary. AD 2014-23-15 required revising the
maintenance program to incorporate new, more restrictive airworthiness
limitations. We issued AD 2014-23-15 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.
AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015),
corresponds to Mandatory Continuing Airworthiness Information (MCAI)
European Aviation Safety Agency Airworthiness Directives 2012-0008,
dated January 16, 2012; and 2013-0147, dated July 16, 2013. You may
examine the MCAI on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by
searching for and locating Docket No. FAA-2015-0489.
Since we issued AD 2014-23-15, Amendment 39-18031 (80 FR 3871,
January 26, 2015), we have determined that certain limitations required
by AD 2014-23-15 conflict with limitations required by AD 2014-26-10,
Amendment 39-18061 (80 FR 2813, January 21, 2015). Paragraph (n) of AD
2014-23-15 requires revising the maintenance or inspection program, as
applicable, to incorporate the airworthiness limitations specified in
paragraphs (n)(1), (n)(2), and (n)(3) of AD 2014-23-15. Paragraph
(n)(3) of AD 2014-23-15 references Airbus A318/A319/A320/A321 ALS Part
4--Ageing Systems Maintenance, dated January 8, 2008. However,
paragraph (g) of AD 2014-26-10 requires revising the maintenance or
inspection program, as applicable, to incorporate Airbus A318/A319/
A320/A321 Airworthiness Limitations Section, ALS Part 4, Aging Systems
Maintenance, Revision 01, dated June 15, 2012.
Airbus A318/A319/A320/A321 Airworthiness Limitations Section, ALS
Part 4, Aging Systems Maintenance, Revision 01, dated June 15, 2012,
contains the most recent airworthiness limitations for ALS Part 4.
Therefore, Airbus A318/A319/A320/A321 ALS Part 4--Ageing Systems
Maintenance, dated January 8, 2008, should not be incorporated as
required by AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26,
2015). We have removed paragraph (n)(3) of AD 2014-23-15 from this AD.
We have also revised the introductory text of paragraph (n) of this AD
to refer only to paragraphs (n)(1) and (n)(2) of this AD.
FAA's Determination and Requirements of This 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 issuing this
[[Page 15153]]
AD because we evaluated all pertinent information and determined the
unsafe condition exists and is likely to exist or develop on other
products of these same type designs.
FAA's Determination of the Effective Date
An unsafe condition exists that requires the immediate adoption of
this AD. The FAA has found that the risk to the flying public justifies
waiving notice and comment prior to adoption of this rule because
operators must comply with the most recent airworthiness limitations,
which are specified in Airbus A318/A319/A320/A321 ALS Part 4--Ageing
Systems Maintenance, Revision 01, dated June 15, 2012, as required by
AD 2014-26-10, Amendment 39-18061 (80 FR 2813, January 21, 2015). Since
AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015),
requires an earlier version of the airworthiness limitations, i.e.,
Airbus A318/A319/A320/A321 ALS Part 4--Ageing Systems Maintenance,
dated January 8, 2008, we must remove that requirement in order to
avoid a conflict with certain requirements of AD 2014-26-10. Therefore,
we determined that notice and opportunity for public comment before
issuing this AD are impracticable and that good cause exists for making
this amendment effective in fewer than 30 days.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2015-0489; Directorate
Identifier 2015-NM-013-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
those comments.
We will post all comments we receive, without change, to <a href="http://www.regulations.gov">http://www.regulations.gov</a>, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Costs of Compliance
We estimate that this AD affects 851 airplanes of U.S. registry.
The actions required by AD 2014-23-15, Amendment 39-18031 (80 FR
3871, January 26, 2015), and retained in this AD take about 2 work-
hours per product, at an average labor rate of $85 per work-hour. Based
on these figures, the estimated cost of the actions that were required
by AD 2014-23-15 is $170 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), and
adding the following new AD:
2015-05-02 Airbus: Amendment 39-18112. Docket No. FAA-2015-0489;
Directorate Identifier 2015-NM-013-AD.
(a) Effective Date
This AD becomes effective March 23, 2015.
(b) Affected ADs
This AD replaces AD 2014-23-15, Amendment 39-18031 (80 FR 3871,
January 26, 2015).
(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 certain limitations
required by AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January
26, 2015), conflict with limitations required by AD 2014-26-10,
Amendment 39-18061 (80 FR 2813, January 21, 2015). We are issuing
this AD to prevent fatigue cracking, accidental damage, or corrosion
in principal structural elements, and possible failure of certain
life limited parts, which could result in reduced structural
integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Revision of Airworthiness Limitations Section (ALS) to
Incorporate Safe Life Airworthiness Limitation Items (ALIs), With No
Changes
This paragraph restates the requirements of paragraph (g) of AD
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), with
no changes. 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
[[Page 15154]]
the ALS of the Instructions for Continued Airworthiness to
incorporate Sub-part 1-2, Life Limits, and Sub-part 1-3,
Demonstrated Fatigue Lives, of Airbus A318/A319/A320/A321 ALS Part
1--Safe Life Airworthiness Limitation Items, Revision 00, dated
February 28, 2006. Accomplish the actions in Sub-part 1-2, Life
Limits, and Sub-part 1-3, Demonstrated Fatigue Lives, of Airbus
A318/A319/A320/A321 ALS Part 1--Safe Life Airworthiness Limitation
Items, Revision 00, dated February 28, 2006, at the times specified
in Sub-part 1-2, Life Limits, and Sub-part 1-3, Demonstrated Fatigue
Lives, of Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, dated February 28, 2006, except as
provided by paragraph (i) of this AD. Accomplishing the actions
required by paragraph (j) of this AD terminates the requirements of
this paragraph.
(h) Retained Revision of ALS for Certain Airplanes To Incorporate
Damage Tolerant ALIs, With No Changes
This paragraph restates certain provisions of paragraph (h) of
AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015),
with no changes. For Model A318-111 and -112 airplanes; Model A319-
111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model
A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and
Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes; except Model A319 airplanes on which Airbus Modifications
28238, 28162, and 28342 have been incorporated in production: Within
14 days after November 7, 2007 (the effective date of AD 2007-20-05,
Amendment 39-15215 (72 FR 56262, October 3, 2007)), revise the ALS
of the Instructions for Continued Airworthiness to incorporate
Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document
AI/SE-M4/95A.0252/96, Issue 7, dated December 2005 (approved by the
European Aviation Safety Agency (EASA) on February 7, 2006); Issue
08, dated March 2006 (approved by the EASA on January 4, 2007); or
Issue 09, dated November 2006 (approved by the EASA on May 21,
2007). Accomplish the actions in Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue
7, dated December 2005; Issue 08, dated March 2006; or Issue 09,
dated November 2006; at the times specified in Airbus A318/A319/
A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/
95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March
2006; or Issue 09, dated November 2006; as applicable; except as
provided by paragraph (i) of this AD. Accomplishing the actions
required by paragraph (j) or (n) of this AD, as applicable,
terminates the requirements of this paragraph.
(i) Retained Grace Period for New or More Restrictive Actions, With No
Changes
This paragraph restates certain provisions of paragraph (i) of
AD 2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015),
with no changes. For Model A318-111 and -112 airplanes; Model A319-
111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model
A320-111, -211, -212, -214, -231, -232, and -233 airplanes; and
Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes: For any new or more restrictive life-limit introduced
with Sub-part 1-2, Life Limits, and Sub-part 1-3, Demonstrated
Fatigue Lives, of Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 00, dated February 28,
2006, replace the part at the time specified in Sub-part 1-2, Life
Limits, and Sub-part 1-3, Demonstrated Fatigue Lives, of Airbus
A318/A319/A320/A321 ALS Part 1--Safe Life Airworthiness Limitation
Items, Revision 00, dated February 28, 2006, or within 6 months
after November 7, 2007 (the effective date of AD 2007-20-05,
Amendment 39-15215 (72 FR 56262, October 3, 2007)), whichever is
later. Accomplishing the actions required by paragraph (n) of this
AD terminates the requirements of this paragraph.
(j) Retained Revision of ALS To Incorporate Damage-Tolerant ALIs, With
No Changes
This paragraph restates the requirements of paragraph (j) of AD
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), with
no changes. Within 9 months after August 22, 2011 (the effective
date of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18,
2011)): Revise the maintenance program by incorporating all
maintenance requirements and associated airworthiness limitations
specified in the Airbus A318/A319/A320/A321 Airworthiness Limitation
Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009;
or Issue 11, dated September 2010. Comply with all applicable
maintenance requirements and associated airworthiness limitations
included in Airbus A318/A319/A320/A321 Airworthiness Limitation
Items, Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009;
or Issue 11, dated September 2010; except as provided by paragraph
(k) of this AD. Accomplishing the actions required by this paragraph
terminates the requirements of paragraph (h) of this AD.
Accomplishing the actions required by paragraph (n) of this AD
terminates the requirements of this paragraph.
(k) Retained Special Compliance Times for Certain Tasks, With No
Changes
This paragraph restates the requirements of paragraph (k) of AD
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), with
no changes. For new and more restrictive tasks introduced with
Airbus A318/A319/A320/A321 Airworthiness Limitation Items, Document
AI/SE-M4/95A.0252/96, Issue 10, dated October 2009; or Issue 11,
dated September 2010; as specified in table 1 to paragraph (k) of
this AD: The initial compliance time for doing the tasks is
specified in table 1 to paragraph (k) of this AD. Accomplishing the
actions required by paragraph (n) of this AD terminates the
requirements of this paragraph.
Table 1 to Paragraph (k) of this AD--Compliance Times for Tasks
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Task Applicability (as Compliance time, whichever occurs later
specified in the
applicability column of
the task)
----------------------------------------------------------------------------------------------------------------
545102-01-6...................... Group 19-1A CFM, Group 19- The threshold as defined Within 2,000 flight
1B CFM, and Model A320- in Airbus A318/A319/ cycles or 5,500 flight
200 airplanes with CFM A320/A321 Airworthiness hours, after August 22,
Industrial (CFM)/ Limitation Items, 2011 (the effective
International Aero Document AI/SE-M4/ date of AD 2011-14-06,
Engine (IAE) engines. 95A.0252/96, Issue 10, Amendment 39-16741 (76
dated October 2009; or FR 42024, July 18,
Issue 11, dated 2011)), whichever
September 2010. occurs first.
545102-01-7...................... Model A320-100 series The threshold as defined Within 2,000 flight
airplanes. in Airbus A318/A319/ cycles or 2,000 flight
A320/A321 Airworthiness hours, after August 22,
Limitation Items, 2011 (the effective
Document AI/SE-M4/ date of AD 2011-14-06,
95A.0252/96, Issue 10, Amendment 39-16741 (76
dated October 2009; or FR 42024, July 18,
Issue 11, dated 2011)), whichever
September 2010. occurs first.
[[Page 15155]]
572050-01-1 or alternative task Group 19-1A and Group 19- At the time of the next Within 6 months after
572050-02-1. 1B airplanes. due accomplishment of August 22, 2011 (the
any one of the tasks effective date of AD
572004, 572020, or 2011-14-06, Amendment
572053 as currently 39-16741 (76 FR 42024,
described in the Airbus July 18, 2011)).
A318/A319/A320/A321
Airworthiness
Limitation Items,
Document AI/SE-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 Airbus July 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.
572050-01-5 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 Airbus July 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
572053 as currently 39-16741 (76 FR 42024,
described in the Airbus July 18, 2011)).
A318/A319/A320/A321
Airworthiness
Limitation Items,
Document AI/SE-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 (A318- The threshold/interval Within 100 days after
121 and -122), Group 19- as defined in Airbus August 22, 2011 (the
1A, Group 19-1B, and A318/A319/A320/A321 effective date of AD
Model A320 and A321 Airworthiness 2011-14-06, Amendment
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.
----------------------------------------------------------------------------------------------------------------
[[Page 15156]]
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, With No Changes
This paragraph restates the requirements of paragraph (l) of AD
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), with
no changes. After the actions specified in paragraphs (g) and (h) of
this AD have been accomplished, no alternative life limits,
inspections, or inspection intervals may be used, except as provided
by paragraphs (i) and (m) of this AD, and except as required by
paragraphs (j) and (n) of this AD.
(m) Retained Limitation: No Alternative Life Limits, Inspections, or
Inspection Intervals After Accomplishment of the Actions Specified in
Paragraph (j) of This AD, With No Changes
This paragraph restates the requirements of paragraph (m) of AD
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), with
no changes. 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) Retained Maintenance or Inspection Program Revision, With Changes
This paragraph restates the requirements of paragraph (n) of AD
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015),
except that paragraph (n)(3) of AD 2014-23-15 is not retained.
Within 30 days after March 2, 2015 (the effective date of AD 2014-
23-15), revise the maintenance or inspection program, as applicable,
to incorporate the ALIs specified in paragraphs (n)(1) and (n)(2) of
this AD. The initial compliance time for the accomplishing the
actions is at the applicable time specified in the ALIs specified in
paragraphs (n)(1) and (n)(2) of this AD; or within 4 months after
March 2, 2015 (the effective date of AD 2014-23-15); whichever
occurs later. Accomplishing these actions terminates the
requirements of paragraphs (g), (h), (i), (j), and (k) of this AD.
(1) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 02, dated May 13, 2011.
(2) Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28,
2013.
(o) Retained Limitation: No Alternative Actions, Intervals, and/or
Critical Design Configuration Control Limitations (CDCCLs), With No
Changes
This paragraph restates the requirements of paragraph (o) of AD
2014-23-15, Amendment 39-18031 (80 FR 3871, January 26, 2015), with
no changes. 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: <a href="/cdn-cgi/l/email-protection#023b2f434c4f2f3333342f434f4d412f5047535747515651426463632c656d74"><span class="__cf_email__" data-cfemail="7940543837345448484f543834363a542b3c282c3c2a2d2a391f1818571e160f">[email protected]</span></a>.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office. The AMOC approval letter must specifically
reference this AD.
(ii) AMOCs approved previously for AD 2011-14-06, Amendment 39-
16741 (76 FR 42024, July 18, 2011), are approved as AMOCs for the
corresponding actions of this AD.
(2) Contacting the Manufacturer: As of March 2, 2015 (the
effective date of AD 2014-23-15, Amendment 39-18031 (80 FR 3871,
January 26, 2015)), for any requirement in this AD to obtain
corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(q) Related Information
Refer to Mandatory Continuing Airworthiness Information (MCAI)
EASA Airworthiness Directives 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-
2015-0489.
(r) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
March 2, 2015 (80 FR 3871, January 26, 2015).
(i) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 02, dated May 13, 2011. The
revision level of this document is identified on only the title page
and in the Record of Revisions. The revision date is not identified
on the title page of this document.
(ii) Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28,
2013. The revision date of this document is not identified on the
title page of this document.
(4) The following service information was approved for IBR on
August 22, 2011 (76 FR 42024, July 18, 2011).
(i) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009. The
revision level of this document is identified on only the title page
and in the Record of Revisions.
(ii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 11, dated September 2010. The
revision level of this document is identified on only the title page
and in the Record of Revisions.
(5) The following service information was approved for IBR on
November 7, 2007 (72 FR 56262, October 3, 2007).
(i) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 00, dated February 28,
2006.
(ii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005.
Note 2 to paragraph (r)(5)(ii) of this AD: This document
contains the following errors: The Summary of Changes is comprised
of 11 pages, which are all identified as Page 2--LEP of Section LEP
instead of Page 1--SOC [through] Page 11--SOC of Section SOC; the
List of Effective Pages only refers to Page 1--SOC for the Summary
of Changes. The List of Effective Pages is comprised of two pages,
and both of those pages are identified as Page 2--LEP. The first
page of Section 2 is identified as Page 6 of Section 1 and is not
referred to in the List of Effective Pages.
(iii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 08, dated March 2006.
Note 3 to paragraph (r)(5)(iii) of this AD: This document
contains the following errors: Pages 3--ROR and 2--SOC are not
referred to in the List of Effective Pages. The List of Effective
Pages is identified as Pages 1--SOC and 2--SOC, instead of 1--LEP
and 2--LEP. The first page of Section 2 is identified as Page 6 of
Section 1 and is not referred to in the List of Effective Pages.
(iv) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 09, dated November 2006.
(6) For service information identified in this AD, contact
Airbus, Airworthiness
[[Page 15157]]
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
<a href="/cdn-cgi/l/email-protection#365755555943584218575f44415944425e1b53574576575f445443451855595b"><span class="__cf_email__" data-cfemail="ceafadada1bba0bae0afa7bcb9a1bcbaa6e3abafbd8eafa7bcacbbbde0ada1a3">[email protected]</span></a>; Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
(7) You may view this service information at the FAA, Transport
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For
information on the availability of this material at the FAA, call
425-227-1221.
(8) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.
Issued in Renton, Washington, on February 25, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-05731 Filed 3-20-15; 8:45 am]
BILLING CODE 4910-13-P
Source: Official FAA Source ↗
Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
This site is not affiliated with or endorsed by the FAA. Always verify with official sources.
Related Airworthiness Directives
2026-03-10
final ruleAirworthiness Directives; Airbus SAS Airplanes
Unsafe Condition: a safety significant latent failure (that is not annunciated), which, in combination with one or more other specific failures or events, could result in a hazardous or catastrophic failure condition.
2025-23-09 Recurring
final ruleAirworthiness Directives; Airbus SAS Airplanes
Unsafe Condition: Cracks on the web horizontal flange and inner cap at frame (FR) 68, left-hand (LH) and right-hand (RH) sides, at stringer (STGR) 22, and additional cracks found at the door stop fitting number 1 ho...
2025-20-15 Recurring
final ruleAirworthiness Directives; Airbus SAS Airplanes
Unsafe Condition: Cracks in the double joggle areas at frame (FR) 16 and FR20, right-hand and left-hand sides, which, if not detected and corrected, could reduce the structural integrity of the fuselage.
2025-20-19 Recurring
final ruleAirworthiness Directives; Airbus SAS Airplanes
Unsafe Condition: fatigue cracking of the forward pressure bulkhead, which could result in reduced structural integrity of the airplane