Airworthiness Directives; Airbus Airplanes, 30492-30498 [2014-12251]
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30492
Federal Register / Vol. 79, No. 102 / Wednesday, May 28, 2014 / Proposed Rules
Service Bulletin 737–53A1325, dated
December 3, 2013, terminates the repetitive
inspections in this AD for the repaired or
modified side only.
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. Amend § 39.13 by adding the
following new airworthiness directive
(AD):
■
The Boeing Company: Docket No. FAA–
2014–0286; Directorate Identifier 2014–
NM–004–AD.
(a) Comments Due Date
We must receive comments by July 14,
2014.
(b) Affected ADs
None.
(c) Applicability
This AD applies to The Boeing Company
Model 737–600 and –700 series airplanes,
certificated in any category, as identified in
Boeing Alert Service Bulletin 737–53A1325,
dated December 3, 2013.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Unsafe Condition
This AD was prompted by reports of
cracking in the body station (STA) 727
bulkhead lower frame. We are issuing this
AD to detect and correct cracking in a
bulkhead lower frame web and inner chord,
which could result in a severed framed and
induced skin cracks, and lead to rapid
decompression of the fuselage.
(j) Post-Repair Inspections
The post-repair inspections, specified in
tables 4, 5, and 6 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1325, dated December 3,
2013, are not required by this AD.
Note 1 to paragraph (j) of this AD: The
damage tolerance inspections specified in
tables 4, 5, and 6 of paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1325, dated December 3,
2013, may be used in support of compliance
with Section 121.1109(c)(2) or 129.109(b)(2)
of the Federal Aviation Regulations (14 CFR
121.1109(c)(2) or 14 CFR 129.109(b)(2)). The
corresponding actions specified in the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1325, dated
December 3, 2013, are not required by this
AD.
(g) Inspections
At the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–53A1325, dated
December 3, 2013, except as provided by
paragraph (i)(1) of this AD: Do a detailed and
open hole high frequency eddy current
(HFEC) inspection of the left- and right-side
lower frame webs and inner chords for
cracking, as applicable, and do all applicable
corrective actions and preventative
modifications, in accordance with the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–53A1325, dated
December 3, 2013, except as required by
paragraph (i)(2) of this AD. Repeat the
applicable inspections required by this
paragraph thereafter at the applicable
intervals specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–53A1325, dated December 3,
2013. Do all applicable corrective actions and
preventative modifications before further
flight.
(k) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Seattle Aircraft
Certification Office (ACO), 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 manager of the ACO, send it to the
attention of the person identified in
paragraph (l)(1) of this AD. Information may
be emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov.
(2) 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(h) Terminating Action
Accomplishment of a modification or a
repair in accordance with Boeing Alert
(l) Related Information
(1) For more information about this AD,
contact Alan Pohl, Aerospace Engineer,
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(i) Exceptions to Service Information
Specifications
(1) Where Boeing Alert Service Bulletin
737–53A1325, dated December 3, 2013,
specifies a compliance time ‘‘after the
original issue date of this service bulletin,’’
this AD requires compliance within the
specified compliance time after the effective
date of this AD.
(2) Where Boeing Alert Service Bulletin
737–53A1325, dated December 3, 2013,
specifies to contact Boeing for appropriate
action: Before further flight, accomplish the
corresponding action using a method
approved in accordance with the procedures
specified in paragraph (k) of this AD.
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Airframe Branch, ANM–120S, FAA, Seattle
Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
phone: (425) 917–6450; fax: (425) 917–6590;
email: alan.pohl@faa.gov.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, P.O. Box 3707, MC 2H–65,
Seattle, WA 98124–2207; telephone 206–
544–5000, extension 1; fax 206–766–5680;
Internet https://www.myboeingfleet.com. You
may view this referenced service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on May 15,
2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–12244 Filed 5–27–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0692; Directorate
Identifier 2012–NM–024–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Supplemental notice of
proposed rulemaking (NPRM);
reopening of comment period.
AGENCY:
We are revising an earlier
proposed airworthiness directive (AD)
for all Airbus Model A318, A319, A320,
and A321 series airplanes. The NPRM
proposed to supersede AD 2011–14–06
and proposed revising the maintenance
program. The NPRM was prompted by
the determination that more restrictive
limitations are necessary. This action
revises the NPRM by revising the
maintenance program to incorporate
new limitations. We are proposing this
AD to prevent fatigue cracking,
accidental damage, or corrosion in
principal structural elements, and
possible failure of certain life limited
parts, which could result in reduced
structural integrity of the airplane. Since
these actions impose an additional
burden over that proposed in the NPRM,
we are reopening the comment period to
allow the public the chance to comment
on these proposed changes.
DATES: We must receive comments on
this proposed AD by July 14, 2014.
SUMMARY:
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Federal Register / Vol. 79, No. 102 / Wednesday, May 28, 2014 / Proposed Rules
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 proposed AD, contact Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet 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.
ADDRESSES:
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Management Facility between 9
a.m. and 5 p.m., Monday through
Friday, except Federal holidays. The AD
docket contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(telephone (800) 647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227–1405;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
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Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2013–0692; Directorate Identifier
2012–NM–024–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
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aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to 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 proposed AD.
Discussion
We proposed to amend 14 CFR part
39 with an earlier NPRM for the
specified products, which was
published in the Federal Register on
August 13, 2013 (78 FR 49213). The
NPRM proposed to supersede AD 2011–
14–06, Amendment 39–16741 (76 FR
42024, July 18, 2011), to require actions
intended to address the unsafe
condition for Airbus Model A318, A319,
A320, and A321 series airplanes.
Since the NPRM (78 FR 49213,
August 13, 2013) was issued, it has been
determined that more restrictive limits
are needed for damage tolerant
airworthiness limitation items. This
supplemental notice of proposed
rulemaking (SNPRM) would require
revising the maintenance program to
incorporate new limitations.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2013–0147,
dated July 16, 2013 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for the specified products. The MCAI
states:
The airworthiness limitations for Airbus
A320 family aeroplanes are currently
included in Airbus A318/A319/A320/A321
Airworthiness Limitations Section (ALS)
document. The airworthiness limitations
applicable to the Damage Tolerant
Airworthiness Limitation Items (DT ALI) are
currently given in Airbus ALS Part 2, which
is approved by EASA.
Previously, EASA issued AD 2010–0071R1
[https://ad.easa.europa.eu/blob/easa_ad_
2010_0071_R1.pdf/AD_2010-0071R1_1]
[associated with FAA AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011)], which required the implementation of
the DT ALI maintenance instructions as
specified in Airbus A318/A319/A320/A321
ALI Document ref. AI/SE–M4/95A.0252/96
issue 10 and Airbus A319 Corporate Jet ALI
Document ref. AI/SE–M2/95A.1038/99.
The new Airbus A318/A319/A320/A321
ALS Part 2 Revision 02, which includes also
Airbus A319 Corporate Jet, introduces more
restrictive DT ALI maintenance instructions.
Failure to comply with these instructions
could result in an unsafe condition.
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30493
Application of new DT ALI tasks 531129–
02–2 and 531129–02–3 introduces initial and
repetitive inspections of the windshield
central lower node continuity fittings,
replacing the one time inspection for that
subject, previously required by EASA AD
2011–0231 [https://ad.easa.europa.eu/blob/
easa_ad_2011_0231.pdf] [associated with
FAA AD 2013–13–03, Amendment 39–17491
(78 FR 41280, July 10, 2013)].
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2010–0071R1 * * *, which are
superseded, and requires compliance with all
maintenance tasks as described in Airbus
A318/A319/A320/A321 ALS part 2 at
Revision 02.
The unsafe condition is fatigue cracking,
accidental damage, or corrosion in
principal structural elements and
possible failure of certain life limited
parts, which could result in reduced
structural integrity of the airplane. You
may examine the MCAI in the AD
docket on the Internet at https://
www.regulations.gov by searching for
and locating it in Docket No. FAA–
2013–0692.
Relevant Service Information
Airbus has issued A318/A319/A320/
A321 ALS Part 2—Damage-Tolerant
Airworthiness Limitation Items (DT
ALI), Revision 02, dated May 28, 2013.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
Comments
We gave the public the opportunity to
comment on the NPRM (78 FR 49213,
August 13, 2013). The following
presents the comments received on the
NPRM and the FAA’s response to each
comment.
Request To Incorporate Airbus A318/
A319/A320/A321 ALS Part 2, Revision
02, Dated May 28, 2013, in Paragraph
(m) of the NPRM (78 FR 49213, August
13, 2013)
American Airlines (AAL) requested
that we either delete the phrase ‘‘doing
the actions required by paragraph (m) of
this AD terminates the requirements of
this paragraph,’’ from paragraph (i) of
the NPRM (78 FR 49213, August 13,
2013), or incorporate Airbus A318/
A319/A320/A321 ALS Part 2—DamageTolerant Airworthiness Limitation Items
(DT ALI), Revision 02, dated May 28,
2013, in paragraph (m) of the NPRM.
The commenter stated that paragraph
(m) of the NPRM does not require
incorporation of Airbus A318/A319/
A320/A321 ALS Part 2, Revision 02,
dated May 28, 2013; therefore,
incorporating paragraph (m) would not
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Federal Register / Vol. 79, No. 102 / Wednesday, May 28, 2014 / Proposed Rules
fully terminate requirements of
paragraph (i) of the NPRM.
We agree to revise the final rule by
adding the incorporation of Airbus
A318/A319/A320/A321 ALS Part 2—
Damage-Tolerant Airworthiness
Limitation Items (DT ALI), Revision 02,
dated May 28, 2013, to paragraph (p) of
this SNPRM.
Request To Incorporate Airbus A318/
A319/A320/A321 ALS Part 3—
Certification Maintenance
Requirements (CMR), Revision 01,
Dated June 15, 2012; in Paragraph (m)
of the NPRM (78 FR 49213, August 13,
2013)
AAL requested that we incorporate
Airbus ALS Part 3—CMR, Revision 01,
dated June 15, 2012; in paragraph (m) of
the NPRM (78 FR 49213, August 13,
2013).
We acknowledge that the latest
approved CMR has been released;
however, we disagree to revise this
SNPRM. EASA has issued a separate AD
2013–0148, dated July 16, 2013 to
require Airbus ALS Part 3—CMR,
Revision 01, dated June 15, 2012.
Therefore, we are considering separate
rulemaking for mandating Airbus ALS
Part 3—CMR, Revision 01, dated June
15, 2012. No change has been made to
this SNPRM in this regard.
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Request To Incorporate Airbus A318/
A319/A320/A321 ALS Part 4—Ageing
Systems Maintenance (ASM), Revision
01, Dated June 15, 2012 in Paragraph
(m) of the NPRM (78 FR 49213, August
13, 2013)
Airbus and AAL requested that we
revise paragraph (m) of the NPRM (78
FR 49213, August 13, 2013) to
incorporate Airbus A318/A319/A320/
A321 ALS Part 4—ASM, Revision 01,
dated June 15, 2012. Airbus stated that
the NPRM mentions Airbus A318/A319/
A320/A321 ALS Part 4—ASM, dated
January 8, 2008; however, Airbus A318/
A319/A320/A321 ALS Part 4—ASM,
Revision 01, dated June 15, 2012,
introduces the extended service goal 1
(ESG1) exercise which allows continued
operation of the A320–200 systems postmodification 39020 at a different
compliance time.
We acknowledge that the latest
approved ALS Part 4 has been released;
however, we disagree to revise this
SNPRM. EASA has issued EASA AD
2013–0146, dated July 16, 2013 to
require Airbus A318/A319/A320/A321
ALS Part 4—ASM, Revision 01, dated
June 15, 2012. Therefore, we might
consider separate rulemaking for
mandating Airbus A318/A319/A320/
A321 ALS Part 4—ASM, Revision 01,
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dated June 15, 2012. No change has
been made to this SNPRM in this regard.
Retained Paragraph of AD 2011–14–06,
Amendment 39–16741 (76 FR 42024,
July 18, 2011)
The NPRM (78 FR 49213, August 13,
2013) did not retain paragraph (h) of AD
2011–14–06, Amendment 39–16741 (76
FR 42024, July 18, 2011). We have
retained that paragraph as paragraph (h)
of this SNPRM and have re-designated
the subsequent paragraphs accordingly.
Differences Between This Proposed AD
and the MCAI or Service Information
The MCAI specifies that if there are
findings from the ALS inspection tasks,
corrective actions must be accomplished
in accordance with Airbus maintenance
documentation. However, this proposed
AD does not include that requirement.
Operators of U.S.-registered airplanes
are required by general airworthiness
and operational regulations to perform
maintenance using methods that are
acceptable to the FAA. We consider
those methods to be adequate to address
any corrective actions necessitated by
the findings of ALS inspections required
by this proposed AD.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
Certain changes described above
expand the scope of the NPRM (78 FR
49213, August 13, 2013). As a result, we
have determined that it is necessary to
reopen the comment period to provide
additional opportunity for the public to
comment on this proposed AD.
Costs of Compliance
We estimate that this proposed AD
affects 851 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD.
The actions that are required by AD
2011–14–06, Amendment 39–16741 (76
FR 42024, July 18, 2011), and retained
in this proposed AD take about 1 workhour per product, at an average labor
rate of $85 per work-hour. Based on
these figures, the estimated cost of the
required actions is $85 per product.
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We also estimate that it would take
about 1 work-hour per product to
comply with the basic requirements of
this proposed AD. The average labor
rate is $85 per work-hour. Based on
these figures, we estimate the cost of
this proposed AD on U.S. operators to
be $72,335, or $85 per product.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
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Federal Register / Vol. 79, No. 102 / Wednesday, May 28, 2014 / Proposed Rules
the FAA proposes to amend 14 CFR part
39 as follows:
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. Amend § 39.13 by removing
Airworthiness Directive (AD) 2011–14–
06, Amendment 39–16741 (76 FR
42024, July 18, 2011) and by adding the
following new AD:
■
Airbus: Docket No. FAA–2013–0692;
Directorate Identifier 2012–NM–024–AD.
(a) Comments Due Date
(h) Retained Revision to ALS To Incorporate
Damage Tolerant ALIs
We must receive comments by July 14,
2014.
(b) Affected ADs
This AD supersedes AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011).
(c) Applicability
This AD applies to all Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–111,
–211, –212, –214, –231, –232, and –233
airplanes; and Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes;
certificated in any category.
(d) Subject
Air Transport Association (ATA) of
America Code 05, Periodic inspections.
(e) Reason
This AD was prompted by a determination
that more restrictive limitations are
necessary. We are issuing this AD to prevent
fatigue cracking, accidental damage, or
corrosion in principal structural elements,
and possible failure of certain life limited
parts, which could result in reduced
structural integrity of the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
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(g) Retained Revision of Airworthiness
Limitations Section (ALS) To Incorporate
Safe Life ALIs
This paragraph restates the requirements of
paragraph (g) of AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011). For Model A318–111 and –112
airplanes; Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes;
Model A320–111, –211, –212, –214, –231,
–232, and –233 airplanes; and Model A321–
111, –112, –131, –211, –212, –213, –231, and
–232 airplanes: Within 3 months after
November 7, 2007 (the effective date of AD
2007–20–05, Amendment 39–15215 (72 FR
56262, October 3, 2007)), revise the ALS of
the Instructions for Continued Airworthiness
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to incorporate Sub-part 1–2, ‘‘Life Limits,’’
and Sub-part 1–3, ‘‘Demonstrated Fatigue
Lives,’’ of Airbus A318/A319/A320/A321
ALS Part 1—Safe Life Airworthiness
Limitation Items, dated February 28, 2006.
Accomplish the actions in Sub-part 1–2,
‘‘Life Limits,’’ and Sub-part 1–3,
‘‘Demonstrated Fatigue Lives,’’ of Airbus
A318/A319/A320/A321 ALS Part 1—Safe
Life Airworthiness Limitation Items, dated
February 28, 2006, at the times specified in
Sub-part 1–2, ‘‘Life Limits,’’ and Sub-part 1–
3, ‘‘Demonstrated Fatigue Lives,’’ of Airbus
A318/A319/A320/A321 ALS Part 1—Safe
Life Airworthiness Limitation Items, dated
February 28, 2006, except as provided by
paragraph (i) of this AD. Doing the actions
required by paragraph (n) of this AD
terminates the requirements of this
paragraph.
This paragraph restates certain provisions
of paragraph (h) of AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011). For Model A318–111 and –112
airplanes; Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes;
Model A320–111, –211, –212, –214, –231,
–232, and –233 airplanes; and Model A321–
111, –112, –131, –211, –212, –213, –231, and
–232 airplanes; except Model A319 airplanes
on which Airbus Modifications 28238,
28162, and 28342 have been incorporated in
production: Within 14 days after November
7, 2007 (the effective date of AD 2007–20–05,
Amendment 39–15215 (72 FR 56262, October
3, 2007)), revise the ALS of the Instructions
for Continued Airworthiness To Incorporate
Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 7, dated
December 2005 (approved by the EASA on
February 7, 2006); Issue 08, dated March
2006 (approved by the EASA on January 4,
2007); or Issue 09, dated November 2006
(approved by the EASA on May 21, 2007).
Accomplish the actions in Airbus A318/
A319/A320/A321 Airworthiness Limitation
Items, Document AI/SE–M4/95A.0252/96,
Issue 7, dated December 2005; Issue 08, dated
March 2006; or Issue 09, dated November
2006; at the times specified in Airbus A318/
A319/A320/A321 Airworthiness Limitation
Items, Document AI/SE–M4/95A.0252/96,
Issue 7, dated December 2005; Issue 08, dated
March 2006; or Issue 09, dated November
2006; as applicable; except as provided by
paragraph (i) of this AD. Doing the actions
required by paragraph (j) of this AD
terminates the requirements of this
paragraph. Doing the actions required by
paragraph (n) of this AD terminates the
requirements of this paragraph.
(i) Retained Grace Period for New or More
Restrictive Actions
This paragraph restates certain provisions
of paragraph (i) of AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011). For Model A318–111 and –112
airplanes; Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes;
Model A320–111, –211, –212, –214, –231,
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Sfmt 4702
30495
–232, and –233 airplanes; and Model A321–
111, –112, –131, –211, –212, –213, –231, and
–232 airplanes: For any new or more
restrictive life limit introduced with Sub-part
1–2, ‘‘Life Limits,’’ and Sub-part 1–3,
‘‘Demonstrated Fatigue Lives,’’ of Airbus
A318/A319/A320/A321 ALS Part 1—Safe
Life Airworthiness Limitation Items, dated
February 28, 2006, replace the part at the
time specified in Sub-part 1–2, ‘‘Life Limits,’’
and Sub-part 1–3, ‘‘Demonstrated Fatigue
Lives,’’ of Airbus A318/A319/A320/A321
ALS Part 1—Safe Life Airworthiness
Limitation Items, dated February 28, 2006, or
within 6 months after November 7, 2007 (the
effective date of AD 2007–20–05,
Amendment 39–15215 (72 FR 56262, October
3, 2007)), whichever is later. Accomplishing
the actions required by paragraph (n) of this
AD terminates the requirements of this
paragraph.
(j) Retained Revision of ALS To Incorporate
Damage-Tolerant ALIs With Revised
Compliance Times
This paragraph restates the requirements of
paragraph (j) of AD 2011–14–06, Amendment
39–16741 (76 FR 42024, July 18, 2011), with
revised compliance times. Within 9 months
after August 22, 2011 (the effective date of
AD 2011–14–06): Revise the maintenance
program by incorporating all maintenance
requirements and associated airworthiness
limitations specified in the Airbus A318/
A319/A320/A321 Airworthiness Limitation
Items, Document AI/SE–M4/95A.0252/96,
Issue 10, dated October 2009; or Issue 11,
dated September 2010. Comply with all
applicable maintenance requirements and
associated airworthiness limitations included
in Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 10, dated
October 2009; or Issue 11, dated September
2010; except as provided by paragraph (k) of
this AD. Doing the actions required by this
paragraph terminates the requirements of
paragraph (h) of this AD. Accomplishing the
actions required by paragraph (n) of this AD
terminates the requirements of this
paragraph.
(k) Retained Special Compliance Times for
Certain Tasks
This paragraph restates the requirements of
paragraph (k) of AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011), with changes to table 1 to paragraph
(k) of this AD. For new and more restrictive
tasks introduced with Airbus A318/A319/
A320/A321 Airworthiness Limitation Items,
Document AI/SE–M4/95A.0252/96, Issue 10,
dated October 2009; or Issue 11, dated
September 2010; as specified in table 1 to
paragraph (k) of this AD: The initial
compliance time for doing the tasks is
specified in table 1 to paragraph (k) of this
AD. Accomplishing the actions specified in
paragraph (n) of this AD terminates the
requirements of this paragraph.
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TABLE 1—TO PARAGRAPH (K) OF THIS AD—COMPLIANCE TIMES FOR TASKS
Applicability
(as specified in
the applicability
column of the task)
545102–01–6 ...................................................................
Group 19–1A CFM, Group
19–1B CFM, and Model
A320–200 airplanes with
CFM Industrial (CFM)/
International Aero Engine (IAE) engines.
545102–01–7 ...................................................................
Model A320–100 series
airplanes.
572050–01–1 or alternative task 572050–02–1 ..............
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 ..............
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Task
Group 21–1A airplanes .....
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Sfmt 4702
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.
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.
E:\FR\FM\28MYP1.SGM
28MYP1
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.
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)).
Federal Register / Vol. 79, No. 102 / Wednesday, May 28, 2014 / Proposed Rules
30497
TABLE 1—TO PARAGRAPH (K) OF THIS AD—COMPLIANCE TIMES FOR TASKS—Continued
Task
Applicability
(as specified in
the applicability
column of the task)
Compliance time, whichever occurs later
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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572050–01–7 or alternative task 572050–02–7 ..............
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.
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.
VerDate Mar<15>2010
18:13 May 27, 2014
Jkt 232001
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.
(l) Retained Limitation: No Alternative Life
Limits, Inspections, or Inspection Intervals
After Accomplishment of the Actions
Specified in Paragraphs (g) and (h) of This
AD
This paragraph restates the requirements of
paragraph (l) of AD 2011–14–06, Amendment
39–16741 (76 FR 42024, July 18, 2011). After
PO 00000
Frm 00013
Fmt 4702
Sfmt 4702
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)).
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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Federal Register / Vol. 79, No. 102 / Wednesday, May 28, 2014 / Proposed Rules
(m) Retained Limitation: No Alternative Life
Limits, Inspections, or Inspection Intervals
After Accomplishment of the Actions
Specified in Paragraph (j) of This AD
This paragraph restates the requirements of
paragraph (m) of AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011). After the actions specified in
paragraph (j) of this AD have been
accomplished, no alternative life limits,
inspections, or inspection intervals may be
used, except as required by paragraph (n) of
this AD.
(n) New Maintenance or Inspection Program
Revision
Within 30 days after the effective date of
this AD, revise the maintenance or inspection
program, as applicable, to incorporate the
Airworthiness Limitation Items specified in
paragraphs (n)(1), (n)(2), and (n)(3) of this
AD. The initial compliance time for the
accomplishing the actions is at the applicable
time specified in Airworthiness Limitation
Items specified in paragraphs (n)(1), (n)(2),
and (n)(3) of this AD; or within 4 months
after the effective date of this AD; whichever
occurs later. Doing these actions terminates
the requirements of paragraphs (g), (h), (i), (j),
and (k) of this AD.
(1) Airbus A318/A319/A320/A321 ALS
Part 1—Safe Life Airworthiness Limitation
Items, Revision 02, dated May 13, 2011.
(2) Airbus A318/A319/A320/A321 ALS
Part 2—Damage-Tolerant Airworthiness
Limitation Items (DT ALI), Revision 02, dated
May 28, 2013.
(3) Airbus A318/A319/A320/A321 ALS
Part 4—Ageing Systems Maintenance, dated
January 8, 2008.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(o) New Limitation: No Alternative Actions,
Intervals, and/or Critical Design
Configuration Control Limitations (CDCCLs)
After accomplishing the revision required
by paragraph (n) of this AD, no alternative
actions (e.g., inspections), intervals, and/or
CDCCLs may be used unless the actions,
intervals, and/or CDCCLs are approved as an
alternative method of compliance (AMOC) in
accordance with the procedures specified in
paragraph (p)(1) of this AD.
(p) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
VerDate Mar<15>2010
16:35 May 27, 2014
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inspector, the manager of the local flight
standards district office/certificate holding
district office. The AMOC approval letter
must specifically reference this AD. AMOCs
approved previously for AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011), are approved as AMOCs for the
corresponding actions specified in this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer, use these actions if they are
FAA-approved. Corrective actions are
considered FAA-approved if they were
approved by the State of Design Authority (or
its delegated agent, or the DAH with a State
of Design Authority’s design organization
approval). You are required to ensure the
product is airworthy before it is returned to
service.
(q) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2012–0008, dated
January 16, 2012; and 2013–0147, dated July
16, 2013; for related information. This MCAI
may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating it in Docket No.
FAA–2013–0692.
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email 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.
Issued in Renton, Washington, on May 15,
2014.
Michael Kaszycki,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2014–12251 Filed 5–27–14; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2014–0285; Directorate
Identifier 2014–NM–035–AD]
RIN 2120–AA64
Airworthiness Directives; Honeywell
International Inc. Air Data Pressure
Transducers
Federal Aviation
Administration (FAA), DOT.
ACTION: Proposed rule; rescission.
AGENCY:
We propose to rescind
airworthiness directive (AD) 2012–26–
15, which applies to certain Honeywell
International Inc. air data pressure
SUMMARY:
PO 00000
Frm 00014
Fmt 4702
Sfmt 4702
transducers as installed on various
aircraft. AD 2012–26–15 requires doing
various tests or checks of equipment
having certain air data pressure
transducers, removing equipment if
necessary, and reporting the results of
the tests or checks. As an option to the
tests or checks, AD 2012–26–15 allows
removal of affected equipment having
certain air data pressure transducers.
We issued AD 2012–26–15 to detect and
correct inaccuracies of the pressure
sensors, which could result in altitude,
computed airspeed, true airspeed, and
Mach computation errors. AD 2012–26–
15 reported that these errors could
reduce the ability of the flightcrew to
maintain the safe flight of the aircraft
and could result in consequent loss of
control of the aircraft. Since we issued
AD 2012–26–15, we have received new
data indicating that the safety risk is
lower than originally estimated.
DATES: We must receive comments on
this proposed AD by July 14, 2014.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, 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: Deliver to the Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For Honeywell service information
identified in this AD, contact Honeywell
Aerospace, Technical Publications and
Distribution, M/S 2101–201, P.O. Box
52170, Phoenix, AZ 85072–2170;
telephone 602–365–5535; fax 602–365–
5577; Internet https://
www.honeywell.com. 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–2014–
0285; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Office
(phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
E:\FR\FM\28MYP1.SGM
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]]>Agencies
[Federal Register Volume 79, Number 102 (Wednesday, May 28, 2014)]
[Proposed Rules]
[Pages 30492-30498]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2014-12251]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0692; Directorate Identifier 2012-NM-024-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Supplemental notice of proposed rulemaking (NPRM); reopening of
comment period.
-----------------------------------------------------------------------
SUMMARY: We are revising an earlier proposed airworthiness directive
(AD) for all Airbus Model A318, A319, A320, and A321 series airplanes.
The NPRM proposed to supersede AD 2011-14-06 and proposed revising the
maintenance program. The NPRM was prompted by the determination that
more restrictive limitations are necessary. This action revises the
NPRM by revising the maintenance program to incorporate new
limitations. We are proposing this AD to prevent fatigue cracking,
accidental damage, or corrosion in principal structural elements, and
possible failure of certain life limited parts, which could result in
reduced structural integrity of the airplane. Since these actions
impose an additional burden over that proposed in the NPRM, we are
reopening the comment period to allow the public the chance to comment
on these proposed changes.
DATES: We must receive comments on this proposed AD by July 14, 2014.
[[Page 30493]]
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to 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 proposed AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@airbus.com; Internet 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; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-1405;
fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0692;
Directorate Identifier 2012-NM-024-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to 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 proposed AD.
Discussion
We proposed to amend 14 CFR part 39 with an earlier NPRM for the
specified products, which was published in the Federal Register on
August 13, 2013 (78 FR 49213). The NPRM proposed to supersede AD 2011-
14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), to require
actions intended to address the unsafe condition for Airbus Model A318,
A319, A320, and A321 series airplanes.
Since the NPRM (78 FR 49213, August 13, 2013) was issued, it has
been determined that more restrictive limits are needed for damage
tolerant airworthiness limitation items. This supplemental notice of
proposed rulemaking (SNPRM) would require revising the maintenance
program to incorporate new limitations.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2013-0147, dated July 16, 2013 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for the specified
products. The MCAI states:
The airworthiness limitations for Airbus A320 family aeroplanes
are currently included in Airbus A318/A319/A320/A321 Airworthiness
Limitations Section (ALS) document. The airworthiness limitations
applicable to the Damage Tolerant Airworthiness Limitation Items (DT
ALI) are currently given in Airbus ALS Part 2, which is approved by
EASA.
Previously, EASA issued AD 2010-0071R1 [https://ad.easa.europa.eu/blob/easa_ad_2010_0071_R1.pdf/AD_2010-0071R1_1] [associated with FAA AD 2011-14-06, Amendment 39-16741
(76 FR 42024, July 18, 2011)], which required the implementation of
the DT ALI maintenance instructions as specified in Airbus A318/
A319/A320/A321 ALI Document ref. AI/SE-M4/95A.0252/96 issue 10 and
Airbus A319 Corporate Jet ALI Document ref. AI/SE-M2/95A.1038/99.
The new Airbus A318/A319/A320/A321 ALS Part 2 Revision 02, which
includes also Airbus A319 Corporate Jet, introduces more restrictive
DT ALI maintenance instructions. Failure to comply with these
instructions could result in an unsafe condition.
Application of new DT ALI tasks 531129-02-2 and 531129-02-3
introduces initial and repetitive inspections of the windshield
central lower node continuity fittings, replacing the one time
inspection for that subject, previously required by EASA AD 2011-
0231 [https://ad.easa.europa.eu/blob/easa_ad_2011_0231.pdf]
[associated with FAA AD 2013-13-03, Amendment 39-17491 (78 FR 41280,
July 10, 2013)].
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2010-0071R1 * * *, which are superseded, and
requires compliance with all maintenance tasks as described in
Airbus A318/A319/A320/A321 ALS part 2 at Revision 02.
The unsafe condition is fatigue cracking, accidental damage, or
corrosion in principal structural elements and possible failure of
certain life limited parts, which could result in reduced structural
integrity of the airplane. You may examine the MCAI in the AD docket on
the Internet at https://www.regulations.gov by searching for and
locating it in Docket No. FAA-2013-0692.
Relevant Service Information
Airbus has issued A318/A319/A320/A321 ALS Part 2--Damage-Tolerant
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28,
2013. The actions described in this service information are intended to
correct the unsafe condition identified in the MCAI.
Comments
We gave the public the opportunity to comment on the NPRM (78 FR
49213, August 13, 2013). The following presents the comments received
on the NPRM and the FAA's response to each comment.
Request To Incorporate Airbus A318/A319/A320/A321 ALS Part 2, Revision
02, Dated May 28, 2013, in Paragraph (m) of the NPRM (78 FR 49213,
August 13, 2013)
American Airlines (AAL) requested that we either delete the phrase
``doing the actions required by paragraph (m) of this AD terminates the
requirements of this paragraph,'' from paragraph (i) of the NPRM (78 FR
49213, August 13, 2013), or incorporate Airbus A318/A319/A320/A321 ALS
Part 2--Damage-Tolerant Airworthiness Limitation Items (DT ALI),
Revision 02, dated May 28, 2013, in paragraph (m) of the NPRM. The
commenter stated that paragraph (m) of the NPRM does not require
incorporation of Airbus A318/A319/A320/A321 ALS Part 2, Revision 02,
dated May 28, 2013; therefore, incorporating paragraph (m) would not
[[Page 30494]]
fully terminate requirements of paragraph (i) of the NPRM.
We agree to revise the final rule by adding the incorporation of
Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant Airworthiness
Limitation Items (DT ALI), Revision 02, dated May 28, 2013, to
paragraph (p) of this SNPRM.
Request To Incorporate Airbus A318/A319/A320/A321 ALS Part 3--
Certification Maintenance Requirements (CMR), Revision 01, Dated June
15, 2012; in Paragraph (m) of the NPRM (78 FR 49213, August 13, 2013)
AAL requested that we incorporate Airbus ALS Part 3--CMR, Revision
01, dated June 15, 2012; in paragraph (m) of the NPRM (78 FR 49213,
August 13, 2013).
We acknowledge that the latest approved CMR has been released;
however, we disagree to revise this SNPRM. EASA has issued a separate
AD 2013-0148, dated July 16, 2013 to require Airbus ALS Part 3--CMR,
Revision 01, dated June 15, 2012. Therefore, we are considering
separate rulemaking for mandating Airbus ALS Part 3--CMR, Revision 01,
dated June 15, 2012. No change has been made to this SNPRM in this
regard.
Request To Incorporate Airbus A318/A319/A320/A321 ALS Part 4--Ageing
Systems Maintenance (ASM), Revision 01, Dated June 15, 2012 in
Paragraph (m) of the NPRM (78 FR 49213, August 13, 2013)
Airbus and AAL requested that we revise paragraph (m) of the NPRM
(78 FR 49213, August 13, 2013) to incorporate Airbus A318/A319/A320/
A321 ALS Part 4--ASM, Revision 01, dated June 15, 2012. Airbus stated
that the NPRM mentions Airbus A318/A319/A320/A321 ALS Part 4--ASM,
dated January 8, 2008; however, Airbus A318/A319/A320/A321 ALS Part 4--
ASM, Revision 01, dated June 15, 2012, introduces the extended service
goal 1 (ESG1) exercise which allows continued operation of the A320-200
systems post-modification 39020 at a different compliance time.
We acknowledge that the latest approved ALS Part 4 has been
released; however, we disagree to revise this SNPRM. EASA has issued
EASA AD 2013-0146, dated July 16, 2013 to require Airbus A318/A319/
A320/A321 ALS Part 4--ASM, Revision 01, dated June 15, 2012. Therefore,
we might consider separate rulemaking for mandating Airbus A318/A319/
A320/A321 ALS Part 4--ASM, Revision 01, dated June 15, 2012. No change
has been made to this SNPRM in this regard.
Retained Paragraph of AD 2011-14-06, Amendment 39-16741 (76 FR 42024,
July 18, 2011)
The NPRM (78 FR 49213, August 13, 2013) did not retain paragraph
(h) of AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011).
We have retained that paragraph as paragraph (h) of this SNPRM and have
re-designated the subsequent paragraphs accordingly.
Differences Between This Proposed AD and the MCAI or Service
Information
The MCAI specifies that if there are findings from the ALS
inspection tasks, corrective actions must be accomplished in accordance
with Airbus maintenance documentation. However, this proposed AD does
not include that requirement. Operators of U.S.-registered airplanes
are required by general airworthiness and operational regulations to
perform maintenance using methods that are acceptable to the FAA. We
consider those methods to be adequate to address any corrective actions
necessitated by the findings of ALS inspections required by this
proposed AD.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Certain changes described above expand the scope of the NPRM (78 FR
49213, August 13, 2013). As a result, we have determined that it is
necessary to reopen the comment period to provide additional
opportunity for the public to comment on this proposed AD.
Costs of Compliance
We estimate that this proposed AD affects 851 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD.
The actions that are required by AD 2011-14-06, Amendment 39-16741
(76 FR 42024, July 18, 2011), and retained in this proposed AD take
about 1 work-hour per product, at an average labor rate of $85 per
work-hour. Based on these figures, the estimated cost of the required
actions is $85 per product.
We also estimate that it would take about 1 work-hour per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of this proposed AD on U.S. operators to be $72,335, or $85
per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator,
[[Page 30495]]
the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. Amend Sec. 39.13 by removing Airworthiness Directive (AD) 2011-14-
06, Amendment 39-16741 (76 FR 42024, July 18, 2011) and by adding the
following new AD:
Airbus: Docket No. FAA-2013-0692; Directorate Identifier 2012-NM-
024-AD.
(a) Comments Due Date
We must receive comments by July 14, 2014.
(b) Affected ADs
This AD supersedes AD 2011-14-06, Amendment 39-16741 (76 FR
42024, July 18, 2011).
(c) Applicability
This AD applies to all Airbus Model A318-111, -112, -121, and -
122 airplanes; Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes; Model A320-111, -211, -212, -214, -231, -232,
and -233 airplanes; and Model A321-111, -112, -131, -211, -212, -
213, -231, and -232 airplanes; certificated in any category.
(d) Subject
Air Transport Association (ATA) of America Code 05, Periodic
inspections.
(e) Reason
This AD was prompted by a determination that more restrictive
limitations are necessary. We are issuing this AD to prevent fatigue
cracking, accidental damage, or corrosion in principal structural
elements, and possible failure of certain life limited parts, which
could result in reduced structural integrity of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Revision of Airworthiness Limitations Section (ALS) To
Incorporate Safe Life ALIs
This paragraph restates the requirements of paragraph (g) of AD
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). For
Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114,
-115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -
214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131,
-211, -212, -213, -231, and -232 airplanes: Within 3 months after
November 7, 2007 (the effective date of AD 2007-20-05, Amendment 39-
15215 (72 FR 56262, October 3, 2007)), revise the ALS of the
Instructions for Continued Airworthiness to incorporate Sub-part 1-
2, ``Life Limits,'' and Sub-part 1-3, ``Demonstrated Fatigue
Lives,'' of Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, dated February 28, 2006. Accomplish
the actions in Sub-part 1-2, ``Life Limits,'' and Sub-part 1-3,
``Demonstrated Fatigue Lives,'' of Airbus A318/A319/A320/A321 ALS
Part 1--Safe Life Airworthiness Limitation Items, dated February 28,
2006, at the times specified in Sub-part 1-2, ``Life Limits,'' and
Sub-part 1-3, ``Demonstrated Fatigue Lives,'' of Airbus A318/A319/
A320/A321 ALS Part 1--Safe Life Airworthiness Limitation Items,
dated February 28, 2006, except as provided by paragraph (i) of this
AD. Doing the actions required by paragraph (n) of this AD
terminates the requirements of this paragraph.
(h) Retained Revision to ALS To Incorporate Damage Tolerant ALIs
This paragraph restates certain provisions of paragraph (h) of
AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). For
Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114,
-115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -
214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131,
-211, -212, -213, -231, and -232 airplanes; except Model A319
airplanes on which Airbus Modifications 28238, 28162, and 28342 have
been incorporated in production: Within 14 days after November 7,
2007 (the effective date of AD 2007-20-05, Amendment 39-15215 (72 FR
56262, October 3, 2007)), revise the ALS of the Instructions for
Continued Airworthiness To Incorporate Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue
7, dated December 2005 (approved by the EASA on February 7, 2006);
Issue 08, dated March 2006 (approved by the EASA on January 4,
2007); or Issue 09, dated November 2006 (approved by the EASA on May
21, 2007). Accomplish the actions in Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue
7, dated December 2005; Issue 08, dated March 2006; or Issue 09,
dated November 2006; at the times specified in Airbus A318/A319/
A320/A321 Airworthiness Limitation Items, Document AI/SE-M4/
95A.0252/96, Issue 7, dated December 2005; Issue 08, dated March
2006; or Issue 09, dated November 2006; as applicable; except as
provided by paragraph (i) of this AD. Doing the actions required by
paragraph (j) of this AD terminates the requirements of this
paragraph. Doing the actions required by paragraph (n) of this AD
terminates the requirements of this paragraph.
(i) Retained Grace Period for New or More Restrictive Actions
This paragraph restates certain provisions of paragraph (i) of
AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). For
Model A318-111 and -112 airplanes; Model A319-111, -112, -113, -114,
-115, -131, -132, and -133 airplanes; Model A320-111, -211, -212, -
214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131,
-211, -212, -213, -231, and -232 airplanes: For any new or more
restrictive life limit introduced with Sub-part 1-2, ``Life
Limits,'' and Sub-part 1-3, ``Demonstrated Fatigue Lives,'' of
Airbus A318/A319/A320/A321 ALS Part 1--Safe Life Airworthiness
Limitation Items, dated February 28, 2006, replace the part at the
time specified in Sub-part 1-2, ``Life Limits,'' and Sub-part 1-3,
``Demonstrated Fatigue Lives,'' of Airbus A318/A319/A320/A321 ALS
Part 1--Safe Life Airworthiness Limitation Items, dated February 28,
2006, or within 6 months after November 7, 2007 (the effective date
of AD 2007-20-05, Amendment 39-15215 (72 FR 56262, October 3,
2007)), whichever is later. Accomplishing the actions required by
paragraph (n) of this AD terminates the requirements of this
paragraph.
(j) Retained Revision of ALS To Incorporate Damage-Tolerant ALIs With
Revised Compliance Times
This paragraph restates the requirements of paragraph (j) of AD
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), with
revised compliance times. Within 9 months after August 22, 2011 (the
effective date of AD 2011-14-06): Revise the maintenance program by
incorporating all maintenance requirements and associated
airworthiness limitations specified in the Airbus A318/A319/A320/
A321 Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96,
Issue 10, dated October 2009; or Issue 11, dated September 2010.
Comply with all applicable maintenance requirements and associated
airworthiness limitations included in Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue
10, dated October 2009; or Issue 11, dated September 2010; except as
provided by paragraph (k) of this AD. Doing the actions required by
this paragraph terminates the requirements of paragraph (h) of this
AD. Accomplishing the actions required by paragraph (n) of this AD
terminates the requirements of this paragraph.
(k) Retained Special Compliance Times for Certain Tasks
This paragraph restates the requirements of paragraph (k) of AD
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), with
changes to table 1 to paragraph (k) of this AD. For new and more
restrictive tasks introduced with Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document AI/SE-M4/95A.0252/96, Issue
10, dated October 2009; or Issue 11, dated September 2010; as
specified in table 1 to paragraph (k) of this AD: The initial
compliance time for doing the tasks is specified in table 1 to
paragraph (k) of this AD. Accomplishing the actions specified in
paragraph (n) of this AD terminates the requirements of this
paragraph.
[[Page 30496]]
Table 1--To Paragraph (k) of This AD--Compliance Times for Tasks
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Task Applicability.......... Compliance time, whichever occurs later
(as specified in.......
the applicability......
column of the task)....
----------------------------------------------------------------------------------------------------------------
545102-01-6.......................... Group 19-1A CFM, Group The threshold as Within 2,000 flight
19-1B CFM, and Model defined in Airbus A318/ cycles or 5,500 flight
A320-200 airplanes A319/A320/A321 hours, after August
with CFM Industrial Airworthiness 22, 2011 (the
(CFM)/International Limitation Items, effective date of AD
Aero Engine (IAE) Document AI/SE-M4/ 2011-14-06, Amendment
engines. 95A.0252/96, Issue 10, 39-16741 (76 FR 42024,
dated October 2009; or July 18, 2011)),
Issue 11, dated whichever occurs
September 2010. first.
545102-01-7.......................... Model A320-100 series The threshold as Within 2,000 flight
airplanes. defined in Airbus A318/ cycles or 2,000 flight
A319/A320/A321 hours, after August
Airworthiness 22, 2011 (the
Limitation Items, effective date of AD
Document AI/SE-M4/ 2011-14-06, Amendment
95A.0252/96, Issue 10, 39-16741 (76 FR 42024,
dated October 2009; or July 18, 2011)),
Issue 11, dated whichever occurs
September 2010. first.
572050-01-1 or alternative task Group 19-1A and Group At the time of the next Within 6 months after
572050-02-1. 19-1B airplanes. due accomplishment of August 22, 2011 (the
any one of the tasks effective date of AD
572004, 572020, or 2011-14-06, Amendment
572053 as currently 39-16741 (76 FR 42024,
described in the July 18, 2011)).
Airbus A318/A319/A320/
A321 Airworthiness
Limitation Items,
Document AI/SE-M4/
95A.0252/96, Issue 7,
dated December 2005;
Issue 08, dated March
2006; or Issue 09,
dated November 2006.
572050-01-4 or alternative task Model A320-200 series At the time of the next Within 6 months after
572050-02-4. airplanes. due accomplishment of August 22, 2011 (the
any one of the tasks effective date of AD
572004, 572020, or 2011-14-06, Amendment
572053 as currently 39-16741 (76 FR 42024,
described in the July 18, 2011)).
Airbus A318/A319/A320/
A321 Airworthiness
Limitation Items,
Document AI/SE-M4/
95A.0252/96, Issue 7,
dated December 2005;
Issue 08, dated March
2006; or Issue 09,
dated November 2006.
572050-01-5 or alternative task Group 21-1A airplanes.. At the time of the next Within 6 months after
572050-02-5. due accomplishment of August 22, 2011 (the
any one of the tasks effective date of AD
572004, 572020, or 2011-14-06, Amendment
572053 as currently 39-16741 (76 FR 42024,
described in the July 18, 2011)).
Airbus A318/A319/A320/
A321 Airworthiness
Limitation Items,
Document AI/SE-M4/
95A.0252/96, Issue 7,
dated December 2005;
Issue 08, dated March
2006; or Issue 09,
dated November 2006.
[[Page 30497]]
Table 1--To Paragraph (k) of This AD--Compliance Times for Tasks--Continued
----------------------------------------------------------------------------------------------------------------
----------------------------------------------------------------------------------------------------------------
Task Applicability.......... Compliance time, whichever occurs later
(as specified in.......
the applicability......
column of the task)....
----------------------------------------------------------------------------------------------------------------
572050-01-7 or alternative task Model A320-100 series At the time of the next Within 6 months after
572050-02-7. airplanes. due accomplishment of August 22, 2011 (the
any one of the tasks effective date of AD
572004, 572020, or 2011-14-06, Amendment
572053 as currently 39-16741 (76 FR 42024,
described in the July 18, 2011)).
Airbus A318/A319/A320/
A321 Airworthiness
Limitation Items,
Document AI/SE-M4/
95A.0252/96, Issue 7,
dated December 2005;
Issue 08, dated March
2006; or Issue 09,
dated November 2006.
534132-01-1.......................... Model A320 PRE 30748 The threshold/interval Within 100 days after
airplanes. as defined in Airbus August 22, 2011 (the
A318/A319/A320/A321 effective date of AD
Airworthiness 2011-14-06, Amendment
Limitation Items, 39-16741 (76 FR 42024,
Document AI/SE-M4/ July 18, 2011)),
95A.0252/96, Issue 10, without exceeding the
dated October 2009; or previous threshold/
Issue 11, dated interval as defined in
September 2010. Airbus A318/A319/A320/
A321 Airworthiness
Limitation Items,
Document AI/SE-M4/
95A.0252/96, Issue 7,
dated December 2005;
Issue 08, dated March
2006; or Issue 09,
dated November 2006.
531118-01-1.......................... Model A318 (except The threshold/interval Within 100 days after
(A318-121 and -122), as defined in Airbus August 22, 2011 (the
Group 19-1A, Group 19- A318/A319/A320/A321 effective date of AD
1B, and Model A320 and Airworthiness 2011-14-06, Amendment
A321 series airplanes. Limitation Items, 39-16741 (76 FR 42024,
Document AI/SE-M4/ July 18, 2011)),
95A.0252/96, Issue 10, without exceeding the
dated October 2009; or previous threshold/
Issue 11, dated interval as defined in
September 2010. Airbus A318/A319/A320/
A321 Airworthiness
Limitation Items,
Document AI/SE-M4/
95A.0252/96, Issue 7,
dated December 2005;
Issue 08, dated March
2006; or Issue 09,
dated November 2006.
531118-01-1.......................... Model A318-121 and -122 The threshold/interval Within 100 days after
airplanes. as defined in Airbus August 22, 2011 (the
A318/A319/A320/A321 effective date of AD
Airworthiness 2011-14-06, Amendment
Limitation Items, 39-16741 (76 FR 42024,
Document AI/SE-M4/ July 18, 2011)).
95A.0252/96, Issue 10,
dated October 2009; or
Issue 11, dated
September 2010.
----------------------------------------------------------------------------------------------------------------
Note 1 to table 1 to paragraph (k) of this AD: ALI Task 572050
refers to the outer wing dry bay and is comprised of extracts from
three ALI Tasks 572004, 572020, and 572053. The threshold of ALI
Task 572050 for the whole dry bay area is that of the lowest
threshold of the source ALI tasks, i.e., that of ALI Task 572053.
(l) Retained Limitation: No Alternative Life Limits, Inspections, or
Inspection Intervals After Accomplishment of the Actions Specified in
Paragraphs (g) and (h) of This AD
This paragraph restates the requirements of paragraph (l) of AD
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). After
the actions specified in paragraphs (g) and (h) of this AD have been
accomplished, no alternative life limits, inspections, or inspection
intervals may be used, except as provided by paragraphs (i) and (m)
of this AD, and except as required by paragraphs (j) and (n) of this
AD.
[[Page 30498]]
(m) Retained Limitation: No Alternative Life Limits, Inspections, or
Inspection Intervals After Accomplishment of the Actions Specified in
Paragraph (j) of This AD
This paragraph restates the requirements of paragraph (m) of AD
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011). After
the actions specified in paragraph (j) of this AD have been
accomplished, no alternative life limits, inspections, or inspection
intervals may be used, except as required by paragraph (n) of this
AD.
(n) New Maintenance or Inspection Program Revision
Within 30 days after the effective date of this AD, revise the
maintenance or inspection program, as applicable, to incorporate the
Airworthiness Limitation Items specified in paragraphs (n)(1),
(n)(2), and (n)(3) of this AD. The initial compliance time for the
accomplishing the actions is at the applicable time specified in
Airworthiness Limitation Items specified in paragraphs (n)(1),
(n)(2), and (n)(3) of this AD; or within 4 months after the
effective date of this AD; whichever occurs later. Doing these
actions terminates the requirements of paragraphs (g), (h), (i),
(j), and (k) of this AD.
(1) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 02, dated May 13, 2011.
(2) Airbus A318/A319/A320/A321 ALS Part 2--Damage-Tolerant
Airworthiness Limitation Items (DT ALI), Revision 02, dated May 28,
2013.
(3) Airbus A318/A319/A320/A321 ALS Part 4--Ageing Systems
Maintenance, dated January 8, 2008.
(o) New Limitation: No Alternative Actions, Intervals, and/or Critical
Design Configuration Control Limitations (CDCCLs)
After accomplishing the revision required by paragraph (n) of
this AD, no alternative actions (e.g., inspections), intervals, and/
or CDCCLs may be used unless the actions, intervals, and/or CDCCLs
are approved as an alternative method of compliance (AMOC) in
accordance with the procedures specified in paragraph (p)(1) of this
AD.
(p) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD. AMOCs
approved previously for AD 2011-14-06, Amendment 39-16741 (76 FR
42024, July 18, 2011), are approved as AMOCs for the corresponding
actions specified in this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer, use these actions if they
are FAA-approved. Corrective actions are considered FAA-approved if
they were approved by the State of Design Authority (or its
delegated agent, or the DAH with a State of Design Authority's
design organization approval). You are required to ensure the
product is airworthy before it is returned to service.
(q) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2012-0008, dated January 16,
2012; and 2013-0147, dated July 16, 2013; for related information.
This MCAI may be found in the AD docket on the Internet at https://www.regulations.gov by searching for and locating it in Docket No.
FAA-2013-0692.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email 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.
Issued in Renton, Washington, on May 15, 2014.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2014-12251 Filed 5-27-14; 8:45 am]
BILLING CODE 4910-13-P
