Airworthiness Directives; Airbus Airplanes, 15152-15157 [2015-05731]
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Federal Register / Vol. 80, No. 55 / Monday, March 23, 2015 / Rules and Regulations
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
AGENCY:
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:
• Federal eRulemaking Portal: Go to
https://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,
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SUMMARY:
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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 AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airwortheas@airbus.com; Internet https://
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 https://
www.regulations.gov 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
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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 https://
www.regulations.gov 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
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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.
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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 https://
www.regulations.gov, 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,
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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:
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15153
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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
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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 specified in the
applicability column of the task)
Group 19–1A
CFM, and
planes with
International
gines.
545102–01–7 ..........
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545102–01–6 ..........
Model A320–100 series airplanes .......
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16:11 Mar 20, 2015
CFM, Group 19–1B
Model A320–200 airCFM Industrial (CFM)/
Aero Engine (IAE) en-
Jkt 235001
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Compliance time, whichever occurs later
The threshold as defined 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.
The threshold as defined 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.
Within 2,000 flight cycles or 5,500
flight hours, after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)), whichever
occurs first.
Within 2,000 flight cycles or 2,000
flight hours, after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)), whichever
occurs first.
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15155
TABLE 1 TO PARAGRAPH (K) OF THIS AD—COMPLIANCE TIMES FOR TASKS—Continued
Group 19–1A and Group 19–1B airplanes.
572050–01–4 or alternative task
572050–02–4.
Model A320–200 series airplanes .......
572050–01–5 or alternative task
572050–02–5.
Group 21–1A airplanes ........................
572050–01–7 or alternative task
572050–02–7.
Model A320–100 series airplanes .......
534132–01–1 ..........
Model A320 PRE 30748 airplanes ......
531118–01–1 ..........
Model A318 (except (A318–121 and
–122), Group 19–1A, Group 19–1B,
and Model A320 and A321 series
airplanes.
The threshold/interval as defined 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.
531118–01–1 ..........
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572050–01–1 or alternative task
572050–02–1.
Model A318–121 and –122 airplanes ..
The threshold/interval as defined 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.
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At the time of the next due accomplishment of any one of the tasks
572004, 572020, or 572053 as currently described in the 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 time of the next due accomplishment of any one of the tasks
572004, 572020, or 572053 as currently described in the 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 time of the next due accomplishment of any one of the tasks
572004, 572020, or 572053 as currently described in the 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 time of the next due accomplishment of any one of the tasks
572004, 572020, or 572053 as currently described in the 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.
The threshold/interval as defined 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.
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Within 6 months after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)).
Within 6 months after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)).
Within 6 months after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)).
Within 6 months after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)).
Within 100 days after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)), without exceeding the previous threshold/interval as defined in Airbus A318/A319/
A320/A321 Airworthiness Limitation
Items,
Document
AI/SE–M4/
95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March
2006; or Issue 09, dated November
2006.
Within 100 days after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)), without exceeding the previous threshold/interval as defined in Airbus A318/A319/
A320/A321 Airworthiness Limitation
Items,
Document
AI/SE–M4/
95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March
2006; or Issue 09, dated November
2006.
Within 100 days after August 22, 2011
(the effective date of AD 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011)).
23MRR1
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Federal Register / Vol. 80, No. 55 / Monday, March 23, 2015 / Rules and Regulations
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.
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(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
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16:11 Mar 20, 2015
Jkt 235001
(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: 9-ANM-116AMOC-REQUESTS@faa.gov.
(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 https://www.regulations.gov 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.
PO 00000
Frm 00010
Fmt 4700
Sfmt 4700
(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
E:\FR\FM\23MRR1.SGM
23MRR1
Federal Register / Vol. 80, No. 55 / Monday, March 23, 2015 / Rules and Regulations
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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
FEDERAL TRADE COMMISSION
16 CFR Parts 2, 3, and 4
Revisions to Rules of Practice
Federal Trade Commission.
Final rules.
AGENCY:
ACTION:
The Commission is revising
certain of its rules of practice to promote
fairness, flexibility and efficiency in its
investigations, studies, and adjudicative
proceedings. These rule revisions
include a revision to the rule governing
the status of cases in administrative
adjudication following a district court’s
denial of preliminary injunctive relief in
an ancillary proceeding. Other changes
include revisions to the list of
Commission officials who have
authority to modify the terms and
timeframe for compliance with
compulsory process, and a change to the
deadline for the Commission to dispose
of petitions to limit or quash
compulsory process. In addition, the
Commission is updating its procedures
for accessing public records and list of
exempt Privacy Act systems.
DATES: These rule revisions are effective
on March 23, 2015.
FOR FURTHER INFORMATION CONTACT:
Josephine Liu, Attorney, (202) 326–
2170, Office of the General Counsel,
Federal Trade Commission, 600
Pennsylvania Avenue NW., Washington,
DC 20580. For information about the
revisions to 16 CFR part 4, contact G.
Richard Gold, Attorney, (202) 326–3355,
Office of the General Counsel, Federal
Trade Commission, 600 Pennsylvania
Avenue NW., Washington, DC 20580.
mstockstill on DSK4VPTVN1PROD with RULES
SUMMARY:
VerDate Sep<11>2014
16:11 Mar 20, 2015
Jkt 235001
The
Federal Trade Commission is revising
certain rules in parts 2 and 3 of its rules
of practice that govern investigations
and adjudicative proceedings, and is
revising other rules in part 4 of its rules
of practice.
The Commission is amending Rules
2.7 and 2.10 to provide the Office of
Policy Planning (‘‘OPP’’) Director and
Deputy Directors with the authority to
modify the terms of compliance with
compulsory process, alter the meet-andconfer prerequisite, and extend the
deadline for filing a petition to limit or
quash compulsory process. This change
reflects OPP’s role in frequently
conducting and leading studies under
section 6(b) of the FTC Act. The
Commission is also revising Rule 2.10(c)
to impose a 40-day deadline for
disposing of petitions to limit or quash
compulsory process.
In part 3 of its Rules, the Commission
is amending Rule 3.26 to make clear that
administrative litigation will be
suspended if respondents file a
qualifying motion for withdrawal or
dismissal after a district court denies
preliminary injunctive relief in an
ancillary proceeding brought under
section 13(b) of the FTC Act. As
discussed below, the Commission will
continue to follow the 1995 Policy
Statement Regarding Administrative
Merger Litigation Following the Denial
of a Preliminary Injunction 1 and
consider the specific circumstances of
each case when deciding whether to
pursue administrative litigation. In
addition, the Commission is revising the
Part 3 rules to correct typographical
errors, ensure consistency between
sections, clarify paragraph headings,
and make other technical changes.
In part 4 of its Rules, the Commission
is revising the procedures and contact
information for accessing public records
in Rule 4.9, making a technical
correction to Rule 4.11, and updating
the names of exempt Privacy Act
systems in Rule 4.13.
Because these rule revisions relate
solely to agency procedure and practice,
publication for notice and comment is
not required under the Administrative
Procedure Act. 5 U.S.C. 553(b).2 These
rule revisions are effective on March 23,
2015.
SUPPLEMENTARY INFORMATION:
1 Administrative Litigation Following the Denial
of a Preliminary Injunction: Policy Statement, 60 FR
39741 (Aug. 3, 1995).
2 For this reason, the requirements of the
Regulatory Flexibility Act are also inapplicable. 5
U.S.C. 601(2), 604(a). Likewise, the amendments do
not modify any FTC collections of information
within the meaning of the Paperwork Reduction
Act, 44 U.S.C. 3501 et seq.
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Frm 00011
Fmt 4700
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15157
I. Revisions to Rules of Practice for
Nonadjudicative Investigations (Part 2)
In 2012, the Commission undertook
an extensive revision of its rules
governing the conduct of its
investigations.3 The Commission is now
revising certain of those rules to
promote fairness, flexibility, and
efficiency in FTC investigations, which
includes studies conducted under
section 6(b) of the FTC Act.
Rules 2.7(l) and 2.10(a)(5): Officials
With Authority To Modify Compulsory
Process and Extend the Deadline for
Petitions To Quash
The Commission is revising Rules
2.7(l) and 2.10(a)(5) to reflect the fact
that the FTC’s Office of Policy Planning
frequently conducts and leads section
6(b) studies. The Commission is
amending Rule 2.7(l) to include the
Office of Policy Planning Director and
Deputy Directors among the identified
Commission officials authorized to
modify the terms of compliance with
orders to file special reports under
section 6(b) of the FTC Act and other
forms of compulsory process.
Commission rules provide that the
officials designated in Rule 2.7(l) also
have the power to modify the manner
and form of production of electronically
stored information (in Rule 2.7(j)), and
alter the meet-and-confer prerequisite
for filing a petition to limit or quash
compulsory process (in Rule 2.7(k)).
Consistent with these amendments, the
Commission is also revising Rule
2.10(a)(5) to state that the Office of
Policy Planning Director and Deputy
Directors are authorized to extend the
deadline for filing a petition to limit or
quash. The revised rules will better
reflect Commission practice and provide
further flexibility and efficiency for 6(b)
studies and other investigations.
Rule 2.10(c): Disposition of Petitions To
Limit or Quash Compulsory Process
The Commission revised Rule 2.10 in
2012 to eliminate the two-step
procedure for rulings on petitions to
limit or quash compulsory process by
requiring the full Commission to rule on
the petition in the first instance. The
rule also imposed a 30-day deadline for
disposition of the petition. The
Commission received no comments
regarding this provision, and adopted it
as proposed, noting that if the
Commission did not meet the deadline,
the petition would not be automatically
granted or denied.4 To enable sufficient
time for full Commission review of the
merits of the petition, the Commission
3 See
4 77
Rules of Practice, 77 FR 59294 (2012).
FR 59300.
E:\FR\FM\23MRR1.SGM
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]]>Agencies
[Federal Register Volume 80, Number 55 (Monday, March 23, 2015)]
[Rules and Regulations]
[Pages 15152-15157]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[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:
Federal eRulemaking Portal: Go to https://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 AD, contact Airbus,
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44
51; email account.airworth-eas@airbus.com; Internet https://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 https://www.regulations.gov 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 https://www.regulations.gov 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 https://www.regulations.gov, 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: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(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 https://www.regulations.gov 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
account.airworth-eas@airbus.com; Internet https://www.airbus.com.
(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: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
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
