Airworthiness Directives; Airbus Airplanes, 49213-49217 [2013-19528]
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Federal Register / Vol. 78, No. 156 / Tuesday, August 13, 2013 / Proposed Rules
Issued in Kansas City, Missouri, on August
6, 2013.
Earl Lawrence,
Manager, Small Airplane Directorate, Aircraft
Certification Service.
[FR Doc. 2013–19638 Filed 8–12–13; 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: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede
airworthiness directive (AD) 2011–14–
06 that applies to all Airbus Model
A318, A319, A320, and A321 series
airplanes. That AD currently requires
revising the maintenance program.
Since we issued that AD, we have
determined that more restrictive
limitations are necessary. This proposed
AD would require 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.
DATES: We must receive comments on
this proposed AD by September 27,
2013.
SUMMARY:
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
ehiers on DSK2VPTVN1PROD with PROPOSALS-1
ADDRESSES:
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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 review copies of the 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 Operations office 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 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:
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
On June 24, 2011, we issued AD
2011–14–06, Amendment 39–16741 (76
FR 42024, July 18, 2011). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 2011–14–06,
Amendment 39–16741 (76 FR 42024,
July 18, 2011), we have determined that
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49213
more restrictive limitations are
necessary. The European Aviation
Safety Agency (EASA), which is the
Technical Agent for the Member States
of the European Community, has issued
EASA Airworthiness Directive 2012–
0008, dated January 16, 2012 (referred to
after this as ‘‘the MCAI’’), to correct an
unsafe condition for the specified
products. The MCAI states:
The airworthiness limitations for Airbus
aeroplanes are currently published in
Airworthiness Limitations Section (ALS)
documents. The airworthiness limitations
applicable to the Safe Life Airworthiness
Limitation Items (SL ALI) are specified in
Airbus A318/A319/A320/A321 ALS Part 1,
which is approved by the European Aviation
Safety Agency (EASA).
EASA AD 2006–0162 [which corresponds to
FAA AD 2007–20–05, Amendment 39–15215
(72 FR 56262, October 3, 2007) which was
superseded by FAA AD 2011–14–06,
Amendment 39–16741 (76 FR 42024, July 18,
2011)] was issued to require the
implementation of the instructions and
airworthiness limitations as specified in
Airbus A318/A319/A320/A321 ALS Part 1
original issue. Failure to comply with the
instructions of ALS Part 1 could result in an
unsafe condition.
This [EASA] AD retains the requirements of
EASA AD 2006–0162, which is superseded,
extends the applicability by adding the
Models A318–121, A318–122, A320–215 and
A320–216, and requires the implementation
of the instructions and airworthiness
limitations as specified in Airbus A318/
A319/A320/A321 ALS part 1 revision 02,
approved on 13 May 2011.
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. The
required actions also include revising
the maintenance program to include
Airbus A318/A319/A320/A321 ALS
Part 4—Ageing Systems Maintenance,
dated January 8, 2008. You may obtain
further information by examining the
MCAI in the AD docket.
Relevant Service Information
Airbus has issued A318/A319/A320/
A321 ALS Part 1—Safe Life
Airworthiness Limitation Items,
Revision 02, dated May 13, 2011; and
A318/A319/A320/A321 ALS Part 4—
Ageing Systems Maintenance, dated
January 8, 2008. The actions described
in this service information are intended
to correct the unsafe condition
identified in the MCAI.
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
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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.
This proposed AD requires revisions
to certain operator maintenance
documents to include new actions.
Compliance with these actions is
required by section 91.403(c) of the
Federal Aviation Regulations (14 CFR
91.403(c)). For airplanes that have been
previously modified, altered, or repaired
in the areas addressed by these
inspections, an operator might not be
able to accomplish the actions described
in the revisions. In this situation, to
comply with 14 CFR 91.403(c), the
operator must request approval of an
alternative method of compliance
(AMOC) in accordance with the
provisions of paragraph (o) of this
proposed AD. The request should
include a description of changes to the
required inspections that will ensure the
continued damage tolerance of the
affected structure and the continued
operational safety of the airplane.
ehiers on DSK2VPTVN1PROD with PROPOSALS-1
Differences Between This AD and the
MCAI or Service Information
Although the MCAI requires revising
the maintenance program to include the
incorporation of Airbus A318/A319/
A320/A321 ALS Part 1—Safe Life
Airworthiness Limitation Items,
Revision 02, dated May 13, 2011, this
AD also requires revising the
maintenance program to include the
incorporation of Airbus A318/A319/
A320/A321 ALS Part 4—Ageing
Systems Maintenance, dated January 8,
2008. This difference has been
coordinated with EASA.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 851 products of U.S.
registry.
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
currently required actions is $85 per
product.
We estimate that it would take about
1 work-hour per product to comply with
the new basic requirements of this
proposed AD. The average labor rate is
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$85 per work-hour. Based on these
figures, we estimate the cost of the
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 proposed
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.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
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,
the FAA proposes to amend 14 CFR part
39 as follows:
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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)
2011–14–06, Amendment 39–16741 (76
FR 42024, July 18, 2011), and 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 September
27, 2013.
(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
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been 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
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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 (h) of this AD. Doing the actions
required by paragraph (m) of this AD
terminates the requirements of this
paragraph.
(h) 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
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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.
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 (j) of
this AD. Doing the actions required by
paragraph (m) of this AD terminates the
requirements of this paragraph.
(i) 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,
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
(j) 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 (j) of this AD: The initial
compliance time for doing the tasks is
specified in table 1 to paragraph (j) of this
AD.
(j) Retained Special Compliance Times for
Certain Tasks
TABLE 1 TO PARAGRAPH (j) 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
planes.
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.
ehiers on DSK2VPTVN1PROD with PROPOSALS-1
Task
Model A320–200
planes.
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series
series
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air-
air-
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.
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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)).
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TABLE 1 TO PARAGRAPH (j) OF THIS AD—Compliance Times for Tasks—Continued
Task
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
planes.
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 ..................
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.
series
air-
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.
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)).
Note 1 to table 1 to paragraph (j) 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.
ehiers on DSK2VPTVN1PROD with PROPOSALS-1
(k) Retained Limitation: No Alternative Life
Limits, Inspections, or Inspection Intervals
After Accomplishment of the Actions
Specified in Paragraph (g) of This AD
(l) 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 (l) of AD 2011–14–06, Amendment
39–16741 (76 FR 42024, July 18, 2011). After
the actions specified in paragraph (g) of this
AD have been accomplished, no alternative
life limits, inspections, or inspection
intervals may be used, except as provided by
paragraph (h) of this AD, and except as
required by paragraph (m) 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 (i) of this AD have been
accomplished, no alternative life limits,
inspections, or inspection intervals may be
used, except as required by paragraph (m) of
this AD.
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(m) New Maintenance Program Revision
Within 30 days after the effective date of
this AD, revise the maintenance program to
incorporate Airbus A318/A319/A320/A321
ALS Part 1—Safe Life Airworthiness
Limitation Items, Revision 02, dated May 13,
2011; and Airbus A318/A319/A320/A321
ALS Part 4—Ageing Systems Maintenance,
dated January 8, 2008. The initial compliance
time for the accomplishing the actions is at
the applicable time specified in Airbus A318/
A319/A320/A321 ALS Part 1—Safe Life
Airworthiness Limitation Items, Revision 02,
dated May 13, 2011, and Airbus A318/A319/
A320/A321 ALS Part 4—Ageing Systems
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Maintenance, dated January 8, 2008; or
within 4 months after the effective date of
this AD; whichever occurs later.
(n) New Limitation: No Alternative Actions
or Intervals
After accomplishing the revision required
by paragraph (m) of this AD, no alternative
actions (e.g., inspections) or intervals, may be
used unless the actions or intervals are
approved as an alternative method of
compliance (AMOC) in accordance with the
procedures specified in paragraph (o) of this
AD.
ehiers on DSK2VPTVN1PROD with PROPOSALS-1
(o) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, 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
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 in accordance with 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 or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(p) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information European
Aviation Safety Agency (EASA)
Airworthiness Directive 2012–0008, dated
January 16, 2012, and the service information
specified in paragraphs (p)(1)(i) through
(p)(1)(viii) of this AD, for related information.
(i) Airbus A318/A319/A320/A321 ALS Part
1—Safe Life Airworthiness Limitation Items,
Revision 02, dated May 13, 2011.
(ii) Airbus A318/A319/A320/A321 ALS
Part 1—Safe Life Airworthiness Limitation
Items, dated February 28, 2006.
(iii) Airbus A318/A319/A320/A321 ALS
Part 4—Ageing Systems Maintenance, dated
January 8, 2008.
(iv) Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 7, dated
December 2005.
VerDate Mar<15>2010
15:30 Aug 12, 2013
Jkt 229001
(v) Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 08, dated
March 2006.
(vi) Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 09, dated
November 2006.
(vii) Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 10, dated
October 2009.
(viii) Airbus A318/A319/A320/A321
Airworthiness Limitation Items, Document
AI/SE–M4/95A.0252/96, Issue 11, dated
September 2010.
(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.airwortheas@airbus.com; Internet https://
www.airbus.com. You may review copies of
the 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 August
2, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–19528 Filed 8–12–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1069; Directorate
Identifier 2012–NM–044–AD]
RIN 2120–AA64
Airworthiness Directives; the Boeing
Company 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 The Boeing Company Model 727
airplanes, which proposed to supersede
an existing AD. That NPRM proposed to
retain repetitive inspections of the intank fuel boost pump wiring,
installation of sleeving over the in-tank
fuel boost pump wires, repetitive
inspections of a certain electrical wire,
sleeve, and conduit, and applicable
investigative and corrective actions; and
repetitive engine fuel suction feed
operational tests. That NPRM proposed
to also require replacement of the wire
SUMMARY:
PO 00000
Frm 00016
Fmt 4702
Sfmt 4702
49217
bundles for the wing and center fuel
boost pumps, installation of convoluted
liners, and related investigative and
corrective actions if necessary. That
NPRM also proposed to require
replacement of the fuel quantity
indicating system (FQIS) wires; a lowfrequency eddy current inspection for
cracking; and repair if necessary. That
NPRM also proposed to require revising
the maintenance program to incorporate
changes to the airworthiness limitations
section. That NPRM was prompted by a
report of damage found to the sleeve,
jacket, and insulation on an electrical
wire during a repetitive inspection. This
action revises that NPRM by revising
certain compliance times, specifying a
terminating action, and adding a
proposed requirement to incorporate
another change to the airworthiness
limitations section. We are proposing
this supplemental NPRM to prevent
chafing of the fuel boost pump electrical
wiring and leakage of fuel into the
conduit, and to prevent electrical arcing
between the wiring and the surrounding
conduit, which could result in arcthrough of the conduit, and consequent
fire or explosion of the fuel tank. 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 supplemental NPRM by September
27, 2013.
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: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590, between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays.
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
review copies of the referenced service
information at the FAA, Transport
E:\FR\FM\13AUP1.SGM
13AUP1
]]>Agencies
[Federal Register Volume 78, Number 156 (Tuesday, August 13, 2013)]
[Proposed Rules]
[Pages 49213-49217]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-19528]
-----------------------------------------------------------------------
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: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede airworthiness directive (AD) 2011-14-
06 that applies to all Airbus Model A318, A319, A320, and A321 series
airplanes. That AD currently requires revising the maintenance program.
Since we issued that AD, we have determined that more restrictive
limitations are necessary. This proposed AD would require 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.
DATES: We must receive comments on this proposed AD by September 27,
2013.
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 review copies of the 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 Operations office
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 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:
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
On June 24, 2011, we issued AD 2011-14-06, Amendment 39-16741 (76
FR 42024, July 18, 2011). That AD required actions intended to address
an unsafe condition on the products listed above.
Since we issued AD 2011-14-06, Amendment 39-16741 (76 FR 42024,
July 18, 2011), we have determined that more restrictive limitations
are necessary. The European Aviation Safety Agency (EASA), which is the
Technical Agent for the Member States of the European Community, has
issued EASA Airworthiness Directive 2012-0008, dated January 16, 2012
(referred to after this as ``the MCAI''), to correct an unsafe
condition for the specified products. The MCAI states:
The airworthiness limitations for Airbus aeroplanes are currently
published in Airworthiness Limitations Section (ALS) documents. The
airworthiness limitations applicable to the Safe Life Airworthiness
Limitation Items (SL ALI) are specified in Airbus A318/A319/A320/
A321 ALS Part 1, which is approved by the European Aviation Safety
Agency (EASA).
EASA AD 2006-0162 [which corresponds to FAA AD 2007-20-05, Amendment
39-15215 (72 FR 56262, October 3, 2007) which was superseded by FAA
AD 2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011)] was
issued to require the implementation of the instructions and
airworthiness limitations as specified in Airbus A318/A319/A320/A321
ALS Part 1 original issue. Failure to comply with the instructions
of ALS Part 1 could result in an unsafe condition.
This [EASA] AD retains the requirements of EASA AD 2006-0162, which
is superseded, extends the applicability by adding the Models A318-
121, A318-122, A320-215 and A320-216, and requires the
implementation of the instructions and airworthiness limitations as
specified in Airbus A318/A319/A320/A321 ALS part 1 revision 02,
approved on 13 May 2011.
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. The required actions also include revising
the maintenance program to include Airbus A318/A319/A320/A321 ALS Part
4--Ageing Systems Maintenance, dated January 8, 2008. You may obtain
further information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 02, dated May 13, 2011; and
A318/A319/A320/A321 ALS Part 4--Ageing Systems Maintenance, dated
January 8, 2008. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
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
[[Page 49214]]
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.
This proposed AD requires revisions to certain operator maintenance
documents to include new actions. Compliance with these actions is
required by section 91.403(c) of the Federal Aviation Regulations (14
CFR 91.403(c)). For airplanes that have been previously modified,
altered, or repaired in the areas addressed by these inspections, an
operator might not be able to accomplish the actions described in the
revisions. In this situation, to comply with 14 CFR 91.403(c), the
operator must request approval of an alternative method of compliance
(AMOC) in accordance with the provisions of paragraph (o) of this
proposed AD. The request should include a description of changes to the
required inspections that will ensure the continued damage tolerance of
the affected structure and the continued operational safety of the
airplane.
Differences Between This AD and the MCAI or Service Information
Although the MCAI requires revising the maintenance program to
include the incorporation of Airbus A318/A319/A320/A321 ALS Part 1--
Safe Life Airworthiness Limitation Items, Revision 02, dated May 13,
2011, this AD also requires revising the maintenance program to include
the incorporation of Airbus A318/A319/A320/A321 ALS Part 4--Ageing
Systems Maintenance, dated January 8, 2008. This difference has been
coordinated with EASA.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 851 products of U.S. registry.
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 currently
required actions is $85 per product.
We estimate that it would take about 1 work-hour per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Based on these figures, we estimate
the cost of the 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 proposed 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.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
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, 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. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2011-14-06, Amendment 39-16741 (76 FR 42024, July 18, 2011), and 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 September 27, 2013.
(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
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been 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
[[Page 49215]]
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 (h) of this AD. Doing the actions required by paragraph
(m) of this AD terminates the requirements of this paragraph.
(h) 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.
(i) 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 (j) of this AD. Doing the actions required by
paragraph (m) of this AD terminates the requirements of this
paragraph.
(j) 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 (j) 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 (j) of this AD: The initial
compliance time for doing the tasks is specified in table 1 to
paragraph (j) of this AD.
Table 1 to Paragraph (j) 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 The threshold as defined Within 2,000 flight
19-1B CFM, and Model in Airbus A318/A319/A320/ cycles or 5,500 flight
A320-200 airplanes A321 Airworthiness hours, after August 22,
with CFM Industrial Limitation Items, 2011 (the effective date
(CFM)/International Document AI/SE-M4/ of AD 2011-14-06,
Aero Engine (IAE) 95A.0252/96, Issue 10, Amendment 39-16741 (76
engines. dated October 2009; or FR 42024, July 18,
Issue 11, dated 2011)), whichever occurs
September 2010. first.
545102-01-7....................... Model A320-100 series The threshold as defined Within 2,000 flight
airplanes. in Airbus A318/A319/A320/ cycles or 2,000 flight
A321 Airworthiness hours, after August 22,
Limitation Items, 2011 (the effective date
Document AI/SE-M4/ 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 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 39-
572053 as currently 16741 (76 FR 42024, July
described in the Airbus 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 39-
572053 as currently 16741 (76 FR 42024, July
described in the Airbus 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.
[[Page 49216]]
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 39-
572053 as currently 16741 (76 FR 42024, July
described in the Airbus 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 39-
572053 as currently 16741 (76 FR 42024, July
described in the Airbus 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 as Within 100 days after
airplanes. defined in Airbus A318/ August 22, 2011 (the
A319/A320/A321 effective date of AD
Airworthiness Limitation 2011-14-06, Amendment 39-
Items, Document AI/SE-M4/ 16741 (76 FR 42024, July
95A.0252/96, Issue 10, 18, 2011)), without
dated October 2009; or exceeding the previous
Issue 11, dated threshold/interval as
September 2010. 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.
531118-01-1....................... Model A318 (except The threshold/interval as Within 100 days after
(A318-121 and -122), defined in Airbus A318/ August 22, 2011 (the
Group 19-1A, Group 19- A319/A320/A321 effective date of AD
1B, and Model A320 Airworthiness Limitation 2011-14-06, Amendment 39-
and A321 series Items, Document AI/SE-M4/ 16741 (76 FR 42024, July
airplanes. 95A.0252/96, Issue 10, 18, 2011)), without
dated October 2009; or exceeding the previous
Issue 11, dated threshold/interval as
September 2010. 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.
531118-01-1....................... Model A318-121 and - The threshold/interval as Within 100 days after
122 airplanes. defined in Airbus A318/ August 22, 2011 (the
A319/A320/A321 effective date of AD
Airworthiness Limitation 2011-14-06, Amendment 39-
Items, Document AI/SE-M4/ 16741 (76 FR 42024, July
95A.0252/96, Issue 10, 18, 2011)).
dated October 2009; or
Issue 11, dated
September 2010.
----------------------------------------------------------------------------------------------------------------
Note 1 to table 1 to paragraph (j) 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.
(k) Retained Limitation: No Alternative Life Limits, Inspections, or
Inspection Intervals After Accomplishment of the Actions Specified in
Paragraph (g) 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 paragraph (g) of this AD have been
accomplished, no alternative life limits, inspections, or inspection
intervals may be used, except as provided by paragraph (h) of this
AD, and except as required by paragraph (m) of this AD.
(l) 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 (i) of this AD have been
accomplished, no alternative life limits, inspections, or inspection
intervals may be used, except as required by paragraph (m) of this
AD.
(m) New Maintenance Program Revision
Within 30 days after the effective date of this AD, revise the
maintenance program to incorporate Airbus A318/A319/A320/A321 ALS
Part 1--Safe Life Airworthiness Limitation Items, Revision 02, dated
May 13, 2011; and Airbus A318/A319/A320/A321 ALS Part 4--Ageing
Systems Maintenance, dated January 8, 2008. The initial compliance
time for the accomplishing the actions is at the applicable time
specified in Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 02, dated May 13, 2011, and
Airbus A318/A319/A320/A321 ALS Part 4--Ageing Systems
[[Page 49217]]
Maintenance, dated January 8, 2008; or within 4 months after the
effective date of this AD; whichever occurs later.
(n) New Limitation: No Alternative Actions or Intervals
After accomplishing the revision required by paragraph (m) of
this AD, no alternative actions (e.g., inspections) or intervals,
may be used unless the actions or intervals are approved as an
alternative method of compliance (AMOC) in accordance with the
procedures specified in paragraph (o) of this AD.
(o) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, 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 in
accordance with 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 or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(p) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
European Aviation Safety Agency (EASA) Airworthiness Directive 2012-
0008, dated January 16, 2012, and the service information specified
in paragraphs (p)(1)(i) through (p)(1)(viii) of this AD, for related
information.
(i) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, Revision 02, dated May 13, 2011.
(ii) Airbus A318/A319/A320/A321 ALS Part 1--Safe Life
Airworthiness Limitation Items, dated February 28, 2006.
(iii) Airbus A318/A319/A320/A321 ALS Part 4--Ageing Systems
Maintenance, dated January 8, 2008.
(iv) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 7, dated December 2005.
(v) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 08, dated March 2006.
(vi) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 09, dated November 2006.
(vii) Airbus A318/A319/A320/A321 Airworthiness Limitation Items,
Document AI/SE-M4/95A.0252/96, Issue 10, dated October 2009.
(viii) Airbus A318/A319/A320/A321 Airworthiness Limitation
Items, Document AI/SE-M4/95A.0252/96, Issue 11, dated September
2010.
(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 review copies of the 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 August 2, 2013.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-19528 Filed 8-12-13; 8:45 am]
BILLING CODE 4910-13-P
