Airworthiness Directives; Airbus Airplanes, 66772-66777 [2012-27126]
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Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules
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); and
3. 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
Authority: 49 U.S.C. 106(g), 40113, 44701.
[Amended]
2. The FAA amends § 39.13 by adding
the following new AD:
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Rolls-Royce Deutschland Ltd & Co KG
(Formerly Rolls-Royce Deutschland
GmbH, and BMW Rolls-Royce plc):
Docket No. FAA–2012–1100; Directorate
Identifier 2012–NE–29–AD.
(a) Comments Due Date
We must receive comments by January 7,
2013.
(b) Affected Airworthiness Directives (ADs)
None.
(c) Applicability
This AD applies to Rolls-Royce
Deutschland Ltd & Co KG (RRD) BR700–
710A1–10 and BR700–710A2–20 turbofan
engines, all serial numbers, and BR700–
710C4–11 turbofan engines that have either
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Issued in Burlington, Massachusetts, on
October 26, 2012.
Colleen M. D’Alessandro,
Assistant Manager, Engine & Propeller
Directorate, Aircraft Certification Service.
(d) Reason
DEPARTMENT OF TRANSPORTATION
This AD was prompted by service
experience that demonstrated premature
wear of the splined coupling on the fuel
pump. We are issuing this AD to prevent
failure of the engine and loss of the airplane.
(e) Actions and Compliance
Unless already done, do the following.
(1) After the effective date of this AD,
replace the fuel pump splined coupling as
follows and every 4,000 hours time in service
(TIS) thereafter:
(i) If the engine has 3,750 hours TIS or
more, within 250 hours TIS.
(ii) If the engine has less than 3,750 hours
TIS, before reaching 4,000 hours TIS.
(2) If you replaced the engine fuel pump
splined coupling before the effective date of
this AD, replace the fuel pump splined
coupling before reaching 4,000 hours TIS
since last replacement, or before further
flight, whichever comes later.
(f) Installation Prohibition
After the effective date of this AD, do not
approve for return to service any engine with
a fuel pump with an affected splined
coupling that has accumulated 4,000 hours
TIS, or any airplane with an engine with an
affected fuel pump splined coupling installed
that has accumulated 4,000 hours TIS.
(g) Alternative Methods of Compliance
(AMOCs)
The Manager, Engine Certification Office,
FAA, may approve AMOCs to this AD. Use
the procedures found in 14 CFR 39.19 to
make your request.
1. The authority citation for part 39
continues to read as follows:
§ 39.13
of the following hardware configuration
standards engraved on the engine data plate:
(1) standard 710C4–11, RRD Alert NonModification Service Bulletin (NMSB) SB–
BR700–72–101466 standard not
incorporated, or
(2) standard 710C4–11/10, RRD Alert
NMSB SB–BR700–72–101466 standard
incorporated.
(h) Related Information
(1) For more information about this AD,
contact Frederick Zink, Aerospace Engineer,
Engine Certification Office, FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA 01803;
email: frederick.zink@faa.gov; phone: 781–
238–7779; fax: 781–238–7199.
(2) Refer to MCAI Airworthiness Directive
No. 2012–0161, dated August 24, 2012, and
RRD Alert NMSB SB–BR700–72–A900509,
Revision 3, dated August 2, 2012, for related
information.
(3) For service information identified in
this AD, contact Rolls-Royce Deutschland Ltd
& Co KG, Eschenweg 11, Dahlewitz, 15827
Blankenfelde-Mahlow, Germany; telephone:
49 0 33–7086–1883; fax: 49 0 33–7086–3276.
You may review copies of the referenced
service information at the FAA, Engine &
Propeller Directorate, 12 New England
Executive Park, Burlington, MA. For
information on the availability of this
material at the FAA, call 781–238–7125.
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[FR Doc. 2012–27108 Filed 11–6–12; 8:45 am]
BILLING CODE 4910–13–P
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2012–1158; Directorate
Identifier 2011–NM–232–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to all Airbus Model A300
and A310 series airplanes; and Model
A300 B4–600, B4–600R, and F4–600R
series airplanes, and Model A300 C4–
605R Variant F airplanes (collectively
called A300–600 series airplanes). The
existing AD currently requires revising
the Airworthiness Limitations section of
the Instructions for Continued
Airworthiness to incorporate new and
revised structural inspections and
inspection intervals. Since we issued
that AD, Airbus has revised certain ALI
documents, which require more
restrictive maintenance requirements
and airworthiness limitations. This
proposed AD would revise the
maintenance program to incorporate the
limitations section. We are proposing
this AD to prevent fatigue cracking,
damage, or corrosion in principal
structural elements, which could result
in reduced structural integrity of the
airplane.
SUMMARY:
We must receive comments on
this proposed AD by December 24,
2012.
DATES:
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–
ADDRESSES:
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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 SAS–
EAW (Airworthiness Office), 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, Washington.
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.
Dan
Rodina, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton,
Washington 98057–3356; telephone
(425) 227–2125; fax (425) 227–1149.
FOR FURTHER INFORMATION CONTACT:
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–2012–1158; Directorate Identifier
2011–NM–232–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.
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Discussion
On May 2, 2011, we issued AD 2011–
10–17, Amendment 39–16698 (76 FR
27875, May 13, 2011). That AD required
actions intended to address an unsafe
condition on the products listed above.
Since we issued AD 2011–10–17,
Amendment 39–16698 (76 FR 27875,
May 13, 2011), Airbus has revised
certain ALI documents, which require
more restrictive maintenance
requirements and airworthiness
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 2011–
0198, dated October 19, 2011 (referred
to after this as ‘‘the MCAI’’), to correct
an unsafe condition for the specified
products. The MCAI states:
The airworthiness limitations applicable to
the Damage Tolerant Airworthiness
Limitation Items (DT ALIs) are currently
listed in Airbus ALI Documents, which are
referenced in the A300, A310 and A300–600
Airworthiness Limitations Section (ALS) Part
2.
Airbus have recently revised the A300–600
and A310 ALI Documents, and these issues
have been approved by EASA. The Airbus
A300–600 ALI Document issue 13 and
temporary revision (TR) 13.1 and the A310
ALI document issue 08 introduce more
restrictive maintenance requirements and
airworthiness limitations, which have been
identified as mandatory actions for continued
airworthiness.
EASA AD 2009–0155 [which corresponds
to FAA AD 2011–10–17, Amendment 39–
16698 (76 FR 27875, May 13, 2011)] required
compliance with the maintenance
requirements and associated airworthiness
limitations defined in the following
documents:
—AIRBUS A300 ALI Document issue 04,
—AIRBUS A310 ALI Document issue 07,
and
—AIRBUS A300–600 ALI Document issue
12.
For the reasons described, this EASA AD
retains the requirements of EASA AD 2009–
0155, which is superseded, and requires
compliance with the airworthiness
limitations defined in the Airbus A300–600
ALI Document issue 13 and TR13.1, and the
A310 ALI document issue 08.
You may obtain further information by
examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued the following
service information. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
• Airbus A310 Airworthiness
Limitation Items Document, AI/SE–M2/
95A.1309/07, Issue 8, dated October
2010 (for Model A310–203, –204, –221,
–222, –304, –322, –324, and –325
airplanes).
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• Airbus A300–600 Airworthiness
Limitation Items Document, AI/SE–M2/
95A.1310/07, Issue 13, dated October
2010 (Model A300 B4–601, B4–603, B4–
620, B4–622, B4–605R, B4–622R, F4–
605R, F4–622R, and C4–605R Variant F
airplanes).
• Airbus Temporary Revision 13.1,
dated February 2011, to the Airbus
A300–600 Airworthiness Limitation
Items Document, AI/SE–M2/95A.1310/
07, Issue 13, dated October 2010 (for
Model A300 B4–601, B4–603, B4–620,
B4–622, B4–605R, B4–622R, F4–605R,
F4–622R, and C4–605R Variant F
airplanes).
FAA’s Determination and Requirements
of This Proposed AD
These products have 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 these same
type designs.
This proposed AD requires revisions
to certain operator maintenance
documents to include new actions (e.g.,
inspections). 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 (u)(1) of this
proposed AD. The request should
include a description of changes to the
required actions that will ensure the
continued damage tolerance of the
affected structure.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 170 products of U.S.
registry.
The actions that are required by AD
2011–10–17, Amendment 39–16698 (76
FR 27875, May 13, 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
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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
$14,450, 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.
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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.
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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
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)
2011–10–17, Amendment 39–16698 (76
FR 27875, May 13, 2011), and adding
the following new AD:
Airbus: Docket No. FAA–2012–1158;
Directorate Identifier 2011–NM–232–AD.
(a) Comments Due Date
We must receive comments by December
24, 2012.
(b) Affected ADs
This AD supersedes AD 2011–10–17,
Amendment 39–16698 (76 FR 27875, May 13,
2011), which superseded AD 2007–04–11,
Amendment 39–14943 (72 FR 8604, February
27, 2007); AD 2007–20–03, Amendment 39–
15213 (72 FR 54536, September 26, 2007);
and AD 2007–25–02, Amendment 39–15283
(72 FR 69612, December 10, 2007). AD 2007–
04–11 superseded AD 96–13–11,
Amendment 39–9679 (61 FR 35122, July 5,
1996).
(c) Applicability
This AD applies to all Airbus model
airplanes identified in paragraphs (c)(1),
(c)(2), and (c)(3) of this AD, certificated in
any category.
(1) Model A300 B2–1A, B2–1C, B4–2C,
B2K–3C, B4–103, B2–203, and B4–203
airplanes.
(2) Model A310–203, –204, –221, –222,
–304, –322, –324, and –325 airplanes.
(3) Model A300 B4–601, B4–603, B4–620,
B4–622, B4–605R, B4–622R, F4–605R, F4–
622R, and C4–605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 57: Wings.
(e) Reason
This AD was prompted by revisions of
certain Airbus Airworthiness Limitation
Items (ALI) documents, which require more
restrictive maintenance requirements and
airworthiness limitations. We are issuing this
AD to prevent fatigue cracking, damage, or
corrosion in principal structural elements,
which could result in reduced structural
integrity of the airplane.
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(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 Maintenance Program Revision
This paragraph restates the requirements of
paragraph (g) of AD 2011–10–17,
Amendment 39–16698 (76 FR 27875, May 13,
2011). Within one year after August 9, 1996
(the effective date of AD 96–13–11,
Amendment 39–9679 (61 FR 35122, July 5,
1996)), replace the revision of the
maintenance program with the inspections,
inspection intervals, repairs, and
replacements defined in Airbus Industrie
A300 Supplemental Structural Inspection
Document, Revision 2, dated June 1994.
Accomplish the actions specified in the
service bulletins identified in Section 6, ‘‘SB
Reference List,’’ in Airbus Industrie A300
Supplemental Structural Inspection
Document, Revision 2, dated June 1994, at
the times specified in those service bulletins.
The actions are to be accomplished in
accordance with those service bulletins.
Accomplishing the initial ALI tasks required
by paragraph (r) of this AD terminates the
actions required by this paragraph.
(1) For airplanes that have exceeded the
threshold specified in any of the service
bulletins identified in Section 6, ‘‘SB
Reference List,’’ in Airbus Industrie A300
Supplemental Structural Inspection
Document, Revision 2, dated June 1994:
Accomplish the actions specified in those
service bulletins within the grace period
specified in those service bulletins. The grace
period is to be measured from August 9, 1996
(the effective date of AD 96–13–11,
Amendment 39–9679 (61 FR 35122, July 5,
1996)).
(2) For airplanes that have exceeded the
threshold specified in any of the service
bulletins identified in Section 6, ‘‘SB
Reference List,’’ in Airbus Industrie A300
Supplemental Structural Inspection
Document, Revision 2, dated June 1994, and
a grace period is not specified in that service
bulletin: Accomplish the actions specified in
that service bulletin within 1,500 flight
cycles after August 9, 1996 (the effective date
of AD 96–13–11, Amendment 39–9679 (61
FR 35122, July 5, 1996)).
(h) Retained Revision of the Maintenance
Inspection Program
This paragraph restates the requirements of
paragraphs (h) and (i) of AD 2011–10–17,
Amendment 39–16698 (76 FR 27875, May 13,
2011).
(1) For airplanes identified in paragraph
(c)(1) of this AD: Within 12 months after
April 3, 2007 (the effective date of AD 2007–
04–11, Amendment 39–14943 (72 FR 8604,
February 27, 2007), replace the revision of
the maintenance program required by
paragraph (g) of this AD with the
supplemental structural inspections,
inspection intervals, and repairs defined in
Airbus A300 Airworthiness Limitation Items
Document SEM2/95A.1090/05, Issue 3, dated
September 2005, as revised by Airbus A300
Temporary Revision (TR) 3.1, dated April
2006. Accomplish the actions specified in
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Airbus A300 Airworthiness Limitation Items
Document SEM2/95A.1090/05, Issue 3, dated
September 2005, as revised by Airbus A300
TR 3.1, dated April 2006, at the times
specified in that ALI, except as provided by
paragraph (h)(2) of this AD. The actions must
be accomplished in accordance with Airbus
A300 Airworthiness Limitation Items
Document SEM2/95A.1090/05, Issue 3, dated
September 2005, as revised by Airbus A300
TR 3.1, dated April 2006. Accomplishing the
initial ALI tasks required by paragraph (r) of
this AD terminates the actions required by
this paragraph.
(2) For airplanes identified in paragraph
(c)(1) of this AD that have exceeded the
threshold or intervals specified in the Airbus
A300 Airworthiness Limitation Items
Document SEM2/95A.1090/05, Issue 3, dated
September 2005, for the application tolerance
on the first interval for new and revised
requirements and have exceeded 50 percent
of the intervals specified in sections D and
E of Airbus A300 Airworthiness Limitation
Items Document SEM2/95A.1090/05, Issue 3,
dated September 2005: Do the actions within
6 months after April 3, 2007 (the effective
date of AD 2007–04–11, Amendment 39–
14943 (72 FR 8604, February 27, 2007)).
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(i) Retained Corrective Actions
This paragraph restates the requirements of
paragraph (j) of AD 2011–10–17, Amendment
39–16698 (76 FR 27875, May 13, 2011).
Damaged, cracked, or corroded structure
detected during any inspection done in
accordance with the Airbus A300
Airworthiness Limitation Items Document
SEM2/95A.1090/05, Issue 3, dated September
2005, must be repaired, before further flight,
in accordance with Airbus A300
Airworthiness Limitation Items Document
SEM2/95A.1090/05, Issue 3, dated September
2005, as revised by Airbus A300 TR 3.1,
dated April 2006, except as provided by
paragraph (j) of this AD; or other data
meeting the certification basis of the airplane
which is approved by the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or by the
European Aviation Safety Agency (EASA) (or
its delegated agent).
(j) Retained Exception
This paragraph restates the requirements of
paragraph (k) of AD 2011–10–17,
Amendment 39–16698 (76 FR 27875, May 13,
2011). Where the Airbus A300 Airworthiness
Limitation Items Document SEM2/95A.1090/
05, Issue 3, dated September 2005, specifies
contacting Airbus for appropriate action:
Before further flight, repair the damaged,
cracked, or corroded structure using a
method approved by either the Manager,
International Branch, ANM–116; or the
EASA (or its delegated agent).
(k) Retained No Fleet Sampling
This paragraph restates the requirements of
paragraph (l) of AD 2011–10–17, Amendment
39–16698 (76 FR 27875, May 13, 2011).
Although Airbus A300 Airworthiness
Limitation Items Document SEM2/95A.1090/
05, Issue 3, dated September 2005, specifies
to do a ‘‘Sampling Concept’’ in section B, this
AD prohibits the use of such a sampling
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program and requires all affected airplanes of
the fleet to be inspected.
(l) Retained No Reporting
This paragraph restates the exception
specified in paragraph (m) of AD 2011–10–
17, Amendment 39–16698 (76 FR 27875, May
13, 2011). Although Airbus A300
Airworthiness Limitation Items Document
SEM2/95A.1090/05, Issue 3, dated September
2005, specifies to submit certain information
to the manufacturer, this AD does not
include that requirement.
(m) Retained Actions and Compliance
This paragraph restates the requirements of
paragraph (n) of AD 2011–10–17,
Amendment 39–16698 (76 FR 27875, May 13,
2011). For airplanes identified in paragraph
(c)(3) of this AD: Within 3 months after
October 31, 2007 (the effective date AD
2007–20–03, Amendment 39–15213 (72 FR
54536, September 26, 2007)), revise the
Airworthiness Limitations Section (ALS) of
the Instructions for Continued Airworthiness
(ICA) to incorporate Airbus A300–600
Airworthiness Limitation Items Document
AI/SE–M2/95A.0502/06, Issue 11, dated
April 2006. The tolerance (grace period) for
compliance (specified in paragraph 2 of
Section B—Program Rules) with Airbus
A300–600 Airworthiness Limitation Items
Document AI/SE–M2/95A.0502/06, Issue 11,
dated April 2006, is within 2,000 flight
cycles after October 31, 2007 (the effective
date AD 2007–20–03), provided that none of
the following is exceeded. Accomplishing the
initial ALI tasks required by paragraph (r) of
this AD terminates the actions required by
this paragraph.
(1) Thresholds or intervals in the operator’s
current approved maintenance schedule that
are taken from a previous ALI issue, if
existing, and are higher than or equal to those
given in Airbus A300–600 Airworthiness
Limitation Items Document AI/SE–M2/
95A.0502/06, Issue 11, dated April 2006.
(2) 8 months after October 31, 2007 (the
effective date AD 2007–20–03, Amendment
39–15213 (72 FR 54536, September 26,
2007)).
(3) 50 percent of the intervals given in
Airbus A300–600 Airworthiness Limitation
Items Document AI/SE–M2/95A.0502/06,
Issue 11, dated April 2006.
(4) Any application tolerance given in the
task description of Airbus A300–600
Airworthiness Limitation Items Document
AI/SE–M2/95A.0502/06, Issue 11, dated
April 2006.
(n) Retained Revision of the ALS of the ICA
This paragraph restates the requirements of
paragraph (o) of AD 2011–10–17,
Amendment 39–16698 (76 FR 27875, May 13,
2011). For airplanes identified in paragraph
(c)(2) of this AD: Within 3 months after
January 14, 2008 (the effective date of AD
2007–25–02, Amendment 39–15283 (72 FR
69612, December 10, 2007)), do the actions
specified in paragraphs (n)(1) and (n)(2) of
this AD. Accomplishing the initial ALI tasks
required by paragraph (r) of this AD
terminates the actions required by this
paragraph.
(1) Revise the ALS of the ICA to
incorporate the structural inspections and
PO 00000
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Fmt 4702
Sfmt 4702
66775
inspection intervals defined in Airbus A310
Airworthiness Limitations Items Document,
AI/SE–M2/95A.0263/06, Issue 6, dated April
2006 (approved by the EASA on May 31,
2006). Accomplish the actions specified in
Airbus A310 Airworthiness Limitations Items
Document, AI/SE–M2/95A.0263/06, Issue 6,
dated April 2006, at the times specified in
Airbus A310 Airworthiness Limitations Items
Document, AI/SE–M2/95A.0263/06, Issue 6,
dated April 2006, except as provided by
paragraph (o) of this AD. Thereafter, except
as provided by paragraphs (n)(2) and (s) of
this AD, no alternative structural inspection
intervals may be approved. The actions
specified in Airbus A310 Airworthiness
Limitations Items Document, AI/SE–M2/
95A.0263/06, Issue 6, dated April 2006, must
be accomplished in accordance with Airbus
A310 Airworthiness Limitations Items
Document, AI/SE–M2/95A.0263/06, Issue 6,
dated April 2006.
(2) Revise the ALS of the ICA to
incorporate the new and revised structural
inspections and inspection intervals defined
in Airbus TR 6.1, dated November 2006
(approved by the EASA on December 12,
2006), to Airbus A310 Airworthiness
Limitations Items Document, AI/SE–M2/
95A.0263/06, Issue 6, dated April 2006.
Thereafter, except as provided by paragraph
(s) of this AD, no alternative structural
inspection intervals may be approved.
(o) Retained Exception to Issue 6 of the A310
ALI Document
This paragraph restates the requirements of
paragraph (p) of AD 2011–10–17,
Amendment 39–16698 (76 FR 27875, May 13,
2011). The tolerance (grace period) for
compliance with Airbus A310 Airworthiness
Limitations Items Document, AI/SE–M2/
95A.0263/06, Issue 6, dated April 2006, is
within 1,500 flight cycles after January 14,
2008 (the effective date of AD 2007–25–02,
Amendment 39–15283 (72 FR 69612,
December 10, 2007)), provided that none of
the following is exceeded.
(1) Thresholds or intervals in the operator’s
current approved maintenance schedule that
are taken from a previous ALI issue, if
existing, and are higher than or equal to those
given in Airbus A310 Airworthiness
Limitations Items Document, AI/SE–M2/
95A.0263/06, Issue 6, dated April 2006.
(2) 18 months after January 14, 2008 (the
effective date of AD 2007–25–02,
Amendment 39–15283 (72 FR 69612,
December 10, 2007)).
(3) 50 percent of the intervals given in
Airbus A310 Airworthiness Limitations Items
Document, AI/SE–M2/95A.0263/06, Issue 6,
dated April 2006.
(4) Any application tolerance specified in
Section D of Airbus A310 Airworthiness
Limitations Items Document, AI/SE–M2/
95A.0263/06, Issue 6, dated April 2006.
(p) Retained Corrective Actions
This paragraph restates certain
requirements of paragraph (q) of AD 2011–
10–17, Amendment 39–16698 (76 FR 27875,
May 13, 2011). Damaged, cracked, or
corroded structure detected during any
inspection done in accordance with Airbus
A310 Airworthiness Limitations Items
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66776
Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules
Document, AI/SE–M2/95A.0263/06, Issue 6,
dated April 2006, must be repaired, before
further flight, in accordance with Airbus
A310 Airworthiness Limitations Items
Document, AI/SE–M2/95A.0263/06, Issue 6,
dated April 2006; or in accordance with other
data meeting the certification basis of the
airplane that has been approved by either the
Manager, International Branch, ANM–116, or
the EASA (or its delegated agent). Where
Airbus A310 Airworthiness Limitations Items
Document, AI/SE–M2/95A.0263/06, Issue 6,
dated April 2006, specifies to contact Airbus
for appropriate action: Before further flight,
repair the damaged, cracked, or corroded
structure using a method approved by either
the Manager, International Branch, ANM–
116; or the EASA (or its delegated agent).
(q) Retained Reporting Requirement
This paragraph restates the requirements of
paragraph (r) of AD 2011–10–17, Amendment
39–16698 (76 FR 27875, May 13, 2011). If any
damage that exceeds the allowable limits
specified in Airbus A310 Airworthiness
Limitations Items Document, AI/SE–M2/
95A.0263/06, Issue 6, dated April 2006, is
detected during any inspection required by
this AD: At the applicable time specified in
paragraph (q)(1) or (q)(2) of this AD, submit
a report of the finding to Airbus, Customer
Service Directorate, Attn: Department
Manager Maintenance Engineering, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; email:
sched.maint@airbus.com. The report must
include the ALI task reference, airplane serial
number, the number of flight cycles and
flight hours on the airplane, identification of
the affected structure, location and
description of the finding including its size
and orientation, and the circumstance of
detection and inspection method used.
(1) If the inspection was done after January
14, 2008 (the effective date of AD 2007–25–
02, Amendment 39–15283 (72 FR 69612,
December 10, 2007)): Submit the report
within 30 days after the inspection.
(2) If the inspection was accomplished
prior to January 14, 2008 (the effective date
of AD 2007–25–02, Amendment 39–15283
(72 FR 69612, December 10, 2007)): Submit
the report within 30 days after January 14,
2008 (the effective date of AD 2007–25–02).
(r) Retained Revision of the ALS of the ICA
This paragraph restates the requirements of
paragraph (s) of AD 2011–10–17,
Amendment 39–16698 (76 FR 27875, May 13,
2011). Within 3 months after June 17, 2011
(the effective date of AD 2011–10–17): Revise
the maintenance program to incorporate the
structural inspections and inspection
intervals defined in the applicable ALI
document listed in table 1 to paragraph (r) of
this AD. Thereafter, except as provided by
paragraphs (u) and (s) of this AD, no
alternative structural inspections and
inspection intervals may be approved. The
actions must be accomplished in accordance
with the applicable issue of the ALI. The
initial ALI tasks must be done at the times
specified in the applicable ALI document
listed in table 1 to paragraph (r) of this AD.
Accomplishing the applicable initial ALI
tasks constitutes terminating action for the
requirements of paragraphs (g) through (q) of
this AD for that airplane only. Doing the
actions required by paragraph (s) of this AD
terminates the requirements of this
paragraph.
TABLE 1 TO PARAGRAPH (R) OF THIS AD—AIRWORTHINESS LIMITATIONS ITEMS DOCUMENT
Document
A300 ...................................
A310 ...................................
A300–600 ...........................
pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Model
Airbus A300 Airworthiness Limitation Items Document AI/SE–M2/95A.1308/07 .....
Airbus A310 Airworthiness Limitation Items Document AI/SE-M2/95A.1309/07 ......
Airbus A300–600 Airworthiness Limitation Items Document AI/SE-M2/95A.1310/
07.
(s) New Maintenance Program Revision
Within 3 months after the effective date of
this AD, do the applicable revision specified
in paragraph (s)(1) or (s)(2) of this AD. The
initial compliance times for the actions
specified in the documents specified in
paragraphs (s)(3), (s)(4), and (s)(5) of this AD
are at the applicable compliance time
specified in the document specified in
paragraphs (s)(3), (s)(4), and (s)(5) of this AD,
or within 3 months after the effective date of
this AD, whichever occurs later; except for
actions identified in both documents for the
Model A300–600 series airplanes, use the
applicable compliance time specified in
Airbus TR 13.1, dated February 2011, to the
Airbus A300–600 Airworthiness Limitation
Items Document AI/SE–M2/95A.1310/07,
Issue 13, dated October 2010. Accomplishing
the applicable initial actions constitutes
terminating action for the requirements of
paragraph (r) of this AD for that airplane
only.
(1) For Model A310 series airplanes:
Within 3 months after the effective date of
this AD, revise the maintenance program to
incorporate the actions (e.g., modifications
and structural inspections) and compliance
times defined in Airbus A310 Airworthiness
Limitation Items Document AI/SE–M2/
95A.1309/07, Issue 8, dated October 2010.
(2) For Model A300–600 series airplanes:
Within 3 months after the effective date of
this AD, revise the maintenance program to
incorporate the structural inspections and
inspection intervals defined in Airbus A300–
600 Airworthiness Limitation Items
VerDate Mar<15>2010
15:18 Nov 06, 2012
Jkt 229001
Issue
Document AI/SE–M2/95A.1310/07, Issue
13.1, dated February 2011.
(3) For Model A310 series airplanes:
Airbus A310 Airworthiness Limitation Items
Document AI/SE–M2/95A.1309/07, Issue 8,
dated October 2010.
(4) For Model A300–600 series airplanes:
Airbus A300–600 Airworthiness Limitation
Items Document AI/SE–M2/95A.1310/07,
Issue 13, dated October 2010.
(5) TR 13.1, dated February 2011, to the
Airbus A300–600 Airworthiness Limitation
Items Document AI/SE–M2/95A.1310/07,
Issue 13, dated October 2010.
(t) New Alternative Inspections and
Inspection Intervals Limitation
After accomplishing the revision required
by paragraph (s) 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 (u) of this
AD.
(u) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, 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
PO 00000
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Fmt 4702
Sfmt 4702
Date
4
7
12
June 2008.
June 2008.
June 2008.
to the International Branch, send it to ATTN:
Dan Rodina, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, Washington 98057–
3356; telephone (425) 227–2125; 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.
(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.
(v) Related Information
Refer to MCAI EASA Airworthiness
Directive 2011–0198, dated October 19, 2011,
and the service information specified in
paragraphs (v)(1) through (v)(12) of this AD,
for related information.
(1) Airbus A300 Airworthiness Limitation
Items Document AI/SE–M2/95A.1308/07,
Issue 4, dated June 2008.
(2) Airbus A300 Airworthiness Limitation
Items Document SEM2/95A.1090/05,
Revision 3, dated September 2005.
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Federal Register / Vol. 77, No. 216 / Wednesday, November 7, 2012 / Proposed Rules
(3) Airbus A300–600 Airworthiness
Limitation Items Document AI/SE–M2/
95A.0502/06, Revision 11, dated April 2006.
(4) Airbus A300–600 Airworthiness
Limitation Items Document AI/SE–M2/
95A.1310/07, Issue 13, dated October 2010.
(5) Airbus A300–600 Airworthiness
Limitation Items Document AI/SE–M2/
95A.1310/07, Revision 12, dated June 2008.
(6) Airbus A310 Airworthiness Limitation
Items Document AI/SE–M2/95A.1309/07,
Issue 8, dated October 2010.
(7) Airbus A310 Airworthiness Limitation
Items Document AI/SE–M2/95A.1309/07,
Revision 7, dated June 2008.
(8) Airbus A310 Airworthiness Limitations
Items Document AI/SE–M2/95A.0263/06,
Revision 6, dated April 2006.
(9) Airbus Industrie A300 Structural
Inspection Document, Revision 2, dated June
1994.
(10) Airbus Temporary Revision 13.1,
dated February 2011, to Airbus A300–600
Airworthiness Limitation Items Document
AI/SE–M2/95A.1310/07, Revision 13, dated
October 2010.
(11) Airbus Temporary Revision 3.1, dated
April 2006, including attachment, dated
April 2006, and including attachments dated
September 2005, to Airbus A300
Airworthiness Limitation Items, Document
SEM2/95A.1090/05, Issue 3, dated September
2005.
(12) Airbus Temporary Revision 6.1,
including pages 1 and 2 of Section D and
page 1 of Section E, dated November 2006,
to Airbus A310 Airworthiness Limitations
Items Document, AI/SE–M2/95A.0263/06,
Issue 6, dated April 2006.
Issued in Renton, Washington, on October
30, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2012–27126 Filed 11–6–12; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF COMMERCE
Bureau of Industry and Security
Background
15 CFR Parts 764 and 766
[Docket No. 120207107–2565–01]
RIN 0694–AF59
pmangrum on DSK3VPTVN1PROD with PROPOSALS-1
Time Limit for Completion of Voluntary
Self-Disclosures and Revised Notice of
the Institution of Administrative
Enforcement Proceedings
Bureau of Industry and
Security, Commerce.
ACTION: Proposed rule.
AGENCY:
This proposed rule would
require that the final, comprehensive
narrative account required in voluntary
self-disclosures (VSDs) of violations of
the Export Administration Regulations
(EAR) be submitted to the Office of
SUMMARY:
VerDate Mar<15>2010
15:18 Nov 06, 2012
Jkt 229001
Export Enforcement within 180 days of
the initial VSD notification. This
proposed rule also would authorize the
use of delivery services other than
registered or certified mail for providing
notice of the issuance of a charging
letter instituting an administrative
enforcement proceeding under the EAR.
It also would remove the phrase ‘‘if
delivery is refused’’ from a provision
relating to determining the date of
service of notice of a charging letter’s
issuance based on an attempted delivery
to the respondent’s last known address.
The Bureau of Industry and Security is
proposing these changes to be better
able to resolve administrative
enforcement proceedings in a timely
manner and provide more efficient
notice of administrative charging letters.
DATES: Comments must be received no
later than January 7, 2013.
ADDRESSES: You may submit comments
by any of the following methods:
• Federal eRulemaking Portal: https://
www.regulations.gov. The identification
number for this rulemaking is BIS–
2012–0043.
• By email directly to
publiccomments@bis.doc.gov. Include
RIN 0694–AF59 in the subject line.
• By mail or delivery to Regulatory
Policy Division, Bureau of Industry and
Security, U.S. Department of Commerce,
Room 2099B, 14th Street and
Pennsylvania Avenue NW., Washington,
DC 20230. Refer to RIN 0694–AF59.
FOR FURTHER INFORMATION CONTACT:
Special Agent Kirk Flashner, Office of
Export Enforcement, Bureau of Industry
and Security, U.S. Department of
Commerce, Room H4514, 14th Street
and Pennsylvania Avenue NW.,
Washington, DC 20230. Tel: (202) 482–
1208. Facsimile: (202) 482–5889.
SUPPLEMENTARY INFORMATION:
The Bureau of Industry and Security
(BIS), Office of Export Enforcement
(OEE), investigates possible violations of
the Export Administration Regulations
(EAR) and orders, licenses, and
authorizations issued thereunder. These
investigations may result in allegations
of violations that may be settled,
adjudicated in an administrative
enforcement proceeding, or referred to
the Department of Justice for possible
criminal prosecution. This rule
proposes three changes to the EAR. One
change addresses voluntary selfdisclosures in connection with OEE’s
conduct of investigations. The other two
changes address service of notice in
administrative enforcement
proceedings.
PO 00000
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Fmt 4702
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66777
Proposed Change Regarding Voluntary
Self-Disclosures
Section 764.5 of the EAR provides a
procedure whereby parties that believe
that they may have committed a
violation of the EAR can voluntarily
disclose the facts of the potential
violations to OEE. Such disclosures that
meet the requirements of § 764.5
typically are afforded ‘‘great weight’’ by
BIS, relative to other mitigating factors,
in determining what administrative
sanctions, if any, to seek. Section 764.5
requires an initial notification, which is
to include a description of the general
nature and extent of the suspected
violations, and is followed at a later date
by a thorough review and narrative
account of the suspected violations,
including all relevant supporting
documentation. If the person making the
initial notification subsequently
completes the narrative account, the
disclosure is deemed to have been
submitted to OEE on the date of the
initial notification. The date of the
initial notification may be significant
because information provided to OEE
may only be considered a voluntary
disclosure if the information ‘‘is
received by OEE for review prior to the
time that OEE or another United States
Government agency has learned of the
same or substantially similar
information from another source and
has commenced an investigation or
inquiry in connection with that
information.’’ 15 CFR 764.5(b)(3).
Currently, § 764.5 of the EAR does not
include a specific time limit within
which a narrative account must be
submitted to OEE. Too often, initial
notifications are not promptly followed
by comprehensive narrative accounts,
and as a result, OEE must maintain open
files on voluntary disclosures for
extended periods of time without
making sufficient progress towards
resolving the matter disclosed. To
address these situations and promote
expeditious resolution of self-disclosed
violations, BIS proposes to set a 180-day
deadline for persons who have
submitted an initial notification to
complete and submit the final narrative
report to OEE. The Director of OEE
could extend this 180-day time
deadline, at his or her discretion, if U.S.
Government interests would be served
by an extension or upon a showing by
the party making the disclosure that
more time is reasonably necessary to
complete the narrative account. Some
illustrative examples of circumstances
that might warrant additional time
include the following.
• Records or information from
multiple entities and/or jurisdictions are
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]]>Agencies
[Federal Register Volume 77, Number 216 (Wednesday, November 7, 2012)]
[Proposed Rules]
[Pages 66772-66777]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-27126]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2012-1158; Directorate Identifier 2011-NM-232-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 an existing airworthiness directive
(AD) that applies to all Airbus Model A300 and A310 series airplanes;
and Model A300 B4-600, B4-600R, and F4-600R series airplanes, and Model
A300 C4-605R Variant F airplanes (collectively called A300-600 series
airplanes). The existing AD currently requires revising the
Airworthiness Limitations section of the Instructions for Continued
Airworthiness to incorporate new and revised structural inspections and
inspection intervals. Since we issued that AD, Airbus has revised
certain ALI documents, which require more restrictive maintenance
requirements and airworthiness limitations. This proposed AD would
revise the maintenance program to incorporate the limitations section.
We are proposing this AD to prevent fatigue cracking, damage, or
corrosion in principal structural elements, which could result in
reduced structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by December 24,
2012.
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-
[[Page 66773]]
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 SAS-EAW (Airworthiness Office), 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, Washington. 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-2125; 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-2012-1158;
Directorate Identifier 2011-NM-232-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 May 2, 2011, we issued AD 2011-10-17, Amendment 39-16698 (76 FR
27875, May 13, 2011). That AD required actions intended to address an
unsafe condition on the products listed above.
Since we issued AD 2011-10-17, Amendment 39-16698 (76 FR 27875, May
13, 2011), Airbus has revised certain ALI documents, which require more
restrictive maintenance requirements and airworthiness 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 2011-0198, dated October 19, 2011 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
The airworthiness limitations applicable to the Damage Tolerant
Airworthiness Limitation Items (DT ALIs) are currently listed in
Airbus ALI Documents, which are referenced in the A300, A310 and
A300-600 Airworthiness Limitations Section (ALS) Part 2.
Airbus have recently revised the A300-600 and A310 ALI
Documents, and these issues have been approved by EASA. The Airbus
A300-600 ALI Document issue 13 and temporary revision (TR) 13.1 and
the A310 ALI document issue 08 introduce more restrictive
maintenance requirements and airworthiness limitations, which have
been identified as mandatory actions for continued airworthiness.
EASA AD 2009-0155 [which corresponds to FAA AD 2011-10-17,
Amendment 39-16698 (76 FR 27875, May 13, 2011)] required compliance
with the maintenance requirements and associated airworthiness
limitations defined in the following documents:
--AIRBUS A300 ALI Document issue 04,
--AIRBUS A310 ALI Document issue 07, and
--AIRBUS A300-600 ALI Document issue 12.
For the reasons described, this EASA AD retains the requirements
of EASA AD 2009-0155, which is superseded, and requires compliance
with the airworthiness limitations defined in the Airbus A300-600
ALI Document issue 13 and TR13.1, and the A310 ALI document issue
08.
You may obtain further information by examining the MCAI in the AD
docket.
Relevant Service Information
Airbus has issued the following service information. The actions
described in this service information are intended to correct the
unsafe condition identified in the MCAI.
Airbus A310 Airworthiness Limitation Items Document, AI/
SE-M2/95A.1309/07, Issue 8, dated October 2010 (for Model A310-203, -
204, -221, -222, -304, -322, -324, and -325 airplanes).
Airbus A300-600 Airworthiness Limitation Items Document,
AI/SE-M2/95A.1310/07, Issue 13, dated October 2010 (Model A300 B4-601,
B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R
Variant F airplanes).
Airbus Temporary Revision 13.1, dated February 2011, to
the Airbus A300-600 Airworthiness Limitation Items Document, AI/SE-M2/
95A.1310/07, Issue 13, dated October 2010 (for Model A300 B4-601, B4-
603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R
Variant F airplanes).
FAA's Determination and Requirements of This Proposed AD
These products have 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
these same type designs.
This proposed AD requires revisions to certain operator maintenance
documents to include new actions (e.g., inspections). 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
(u)(1) of this proposed AD. The request should include a description of
changes to the required actions that will ensure the continued damage
tolerance of the affected structure.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 170 products of U.S. registry.
The actions that are required by AD 2011-10-17, Amendment 39-16698
(76 FR 27875, May 13, 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
[[Page 66774]]
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 $14,450, 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.
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
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]
2. The FAA amends Sec. 39.13 by removing airworthiness directive
(AD) 2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011), and
adding the following new AD:
Airbus: Docket No. FAA-2012-1158; Directorate Identifier 2011-NM-
232-AD.
(a) Comments Due Date
We must receive comments by December 24, 2012.
(b) Affected ADs
This AD supersedes AD 2011-10-17, Amendment 39-16698 (76 FR
27875, May 13, 2011), which superseded AD 2007-04-11, Amendment 39-
14943 (72 FR 8604, February 27, 2007); AD 2007-20-03, Amendment 39-
15213 (72 FR 54536, September 26, 2007); and AD 2007-25-02,
Amendment 39-15283 (72 FR 69612, December 10, 2007). AD 2007-04-11
superseded AD 96-13-11, Amendment 39-9679 (61 FR 35122, July 5,
1996).
(c) Applicability
This AD applies to all Airbus model airplanes identified in
paragraphs (c)(1), (c)(2), and (c)(3) of this AD, certificated in
any category.
(1) Model A300 B2-1A, B2-1C, B4-2C, B2K-3C, B4-103, B2-203, and
B4-203 airplanes.
(2) Model A310-203, -204, -221, -222, -304, -322, -324, and -325
airplanes.
(3) Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R,
F4-605R, F4-622R, and C4-605R Variant F airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 57: Wings.
(e) Reason
This AD was prompted by revisions of certain Airbus
Airworthiness Limitation Items (ALI) documents, which require more
restrictive maintenance requirements and airworthiness limitations.
We are issuing this AD to prevent fatigue cracking, damage, or
corrosion in principal structural elements, 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 Maintenance Program Revision
This paragraph restates the requirements of paragraph (g) of AD
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). Within
one year after August 9, 1996 (the effective date of AD 96-13-11,
Amendment 39-9679 (61 FR 35122, July 5, 1996)), replace the revision
of the maintenance program with the inspections, inspection
intervals, repairs, and replacements defined in Airbus Industrie
A300 Supplemental Structural Inspection Document, Revision 2, dated
June 1994. Accomplish the actions specified in the service bulletins
identified in Section 6, ``SB Reference List,'' in Airbus Industrie
A300 Supplemental Structural Inspection Document, Revision 2, dated
June 1994, at the times specified in those service bulletins. The
actions are to be accomplished in accordance with those service
bulletins. Accomplishing the initial ALI tasks required by paragraph
(r) of this AD terminates the actions required by this paragraph.
(1) For airplanes that have exceeded the threshold specified in
any of the service bulletins identified in Section 6, ``SB Reference
List,'' in Airbus Industrie A300 Supplemental Structural Inspection
Document, Revision 2, dated June 1994: Accomplish the actions
specified in those service bulletins within the grace period
specified in those service bulletins. The grace period is to be
measured from August 9, 1996 (the effective date of AD 96-13-11,
Amendment 39-9679 (61 FR 35122, July 5, 1996)).
(2) For airplanes that have exceeded the threshold specified in
any of the service bulletins identified in Section 6, ``SB Reference
List,'' in Airbus Industrie A300 Supplemental Structural Inspection
Document, Revision 2, dated June 1994, and a grace period is not
specified in that service bulletin: Accomplish the actions specified
in that service bulletin within 1,500 flight cycles after August 9,
1996 (the effective date of AD 96-13-11, Amendment 39-9679 (61 FR
35122, July 5, 1996)).
(h) Retained Revision of the Maintenance Inspection Program
This paragraph restates the requirements of paragraphs (h) and
(i) of AD 2011-10-17, Amendment 39-16698 (76 FR 27875, May 13,
2011).
(1) For airplanes identified in paragraph (c)(1) of this AD:
Within 12 months after April 3, 2007 (the effective date of AD 2007-
04-11, Amendment 39-14943 (72 FR 8604, February 27, 2007), replace
the revision of the maintenance program required by paragraph (g) of
this AD with the supplemental structural inspections, inspection
intervals, and repairs defined in Airbus A300 Airworthiness
Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September
2005, as revised by Airbus A300 Temporary Revision (TR) 3.1, dated
April 2006. Accomplish the actions specified in
[[Page 66775]]
Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/
05, Issue 3, dated September 2005, as revised by Airbus A300 TR 3.1,
dated April 2006, at the times specified in that ALI, except as
provided by paragraph (h)(2) of this AD. The actions must be
accomplished in accordance with Airbus A300 Airworthiness Limitation
Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, as
revised by Airbus A300 TR 3.1, dated April 2006. Accomplishing the
initial ALI tasks required by paragraph (r) of this AD terminates
the actions required by this paragraph.
(2) For airplanes identified in paragraph (c)(1) of this AD that
have exceeded the threshold or intervals specified in the Airbus
A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue
3, dated September 2005, for the application tolerance on the first
interval for new and revised requirements and have exceeded 50
percent of the intervals specified in sections D and E of Airbus
A300 Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue
3, dated September 2005: Do the actions within 6 months after April
3, 2007 (the effective date of AD 2007-04-11, Amendment 39-14943 (72
FR 8604, February 27, 2007)).
(i) Retained Corrective Actions
This paragraph restates the requirements of paragraph (j) of AD
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). Damaged,
cracked, or corroded structure detected during any inspection done
in accordance with the Airbus A300 Airworthiness Limitation Items
Document SEM2/95A.1090/05, Issue 3, dated September 2005, must be
repaired, before further flight, in accordance with Airbus A300
Airworthiness Limitation Items Document SEM2/95A.1090/05, Issue 3,
dated September 2005, as revised by Airbus A300 TR 3.1, dated April
2006, except as provided by paragraph (j) of this AD; or other data
meeting the certification basis of the airplane which is approved by
the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or by the European Aviation Safety Agency (EASA)
(or its delegated agent).
(j) Retained Exception
This paragraph restates the requirements of paragraph (k) of AD
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). Where
the Airbus A300 Airworthiness Limitation Items Document SEM2/
95A.1090/05, Issue 3, dated September 2005, specifies contacting
Airbus for appropriate action: Before further flight, repair the
damaged, cracked, or corroded structure using a method approved by
either the Manager, International Branch, ANM-116; or the EASA (or
its delegated agent).
(k) Retained No Fleet Sampling
This paragraph restates the requirements of paragraph (l) of AD
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). Although
Airbus A300 Airworthiness Limitation Items Document SEM2/95A.1090/
05, Issue 3, dated September 2005, specifies to do a ``Sampling
Concept'' in section B, this AD prohibits the use of such a sampling
program and requires all affected airplanes of the fleet to be
inspected.
(l) Retained No Reporting
This paragraph restates the exception specified in paragraph (m)
of AD 2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011).
Although Airbus A300 Airworthiness Limitation Items Document SEM2/
95A.1090/05, Issue 3, dated September 2005, specifies to submit
certain information to the manufacturer, this AD does not include
that requirement.
(m) Retained Actions and Compliance
This paragraph restates the requirements of paragraph (n) of AD
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). For
airplanes identified in paragraph (c)(3) of this AD: Within 3 months
after October 31, 2007 (the effective date AD 2007-20-03, Amendment
39-15213 (72 FR 54536, September 26, 2007)), revise the
Airworthiness Limitations Section (ALS) of the Instructions for
Continued Airworthiness (ICA) to incorporate Airbus A300-600
Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue
11, dated April 2006. The tolerance (grace period) for compliance
(specified in paragraph 2 of Section B--Program Rules) with Airbus
A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/
06, Issue 11, dated April 2006, is within 2,000 flight cycles after
October 31, 2007 (the effective date AD 2007-20-03), provided that
none of the following is exceeded. Accomplishing the initial ALI
tasks required by paragraph (r) of this AD terminates the actions
required by this paragraph.
(1) Thresholds or intervals in the operator's current approved
maintenance schedule that are taken from a previous ALI issue, if
existing, and are higher than or equal to those given in Airbus
A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.0502/
06, Issue 11, dated April 2006.
(2) 8 months after October 31, 2007 (the effective date AD 2007-
20-03, Amendment 39-15213 (72 FR 54536, September 26, 2007)).
(3) 50 percent of the intervals given in Airbus A300-600
Airworthiness Limitation Items Document AI/SE-M2/95A.0502/06, Issue
11, dated April 2006.
(4) Any application tolerance given in the task description of
Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/
95A.0502/06, Issue 11, dated April 2006.
(n) Retained Revision of the ALS of the ICA
This paragraph restates the requirements of paragraph (o) of AD
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). For
airplanes identified in paragraph (c)(2) of this AD: Within 3 months
after January 14, 2008 (the effective date of AD 2007-25-02,
Amendment 39-15283 (72 FR 69612, December 10, 2007)), do the actions
specified in paragraphs (n)(1) and (n)(2) of this AD. Accomplishing
the initial ALI tasks required by paragraph (r) of this AD
terminates the actions required by this paragraph.
(1) Revise the ALS of the ICA to incorporate the structural
inspections and inspection intervals defined in Airbus A310
Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06,
Issue 6, dated April 2006 (approved by the EASA on May 31, 2006).
Accomplish the actions specified in Airbus A310 Airworthiness
Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated
April 2006, at the times specified in Airbus A310 Airworthiness
Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated
April 2006, except as provided by paragraph (o) of this AD.
Thereafter, except as provided by paragraphs (n)(2) and (s) of this
AD, no alternative structural inspection intervals may be approved.
The actions specified in Airbus A310 Airworthiness Limitations Items
Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, must be
accomplished in accordance with Airbus A310 Airworthiness
Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated
April 2006.
(2) Revise the ALS of the ICA to incorporate the new and revised
structural inspections and inspection intervals defined in Airbus TR
6.1, dated November 2006 (approved by the EASA on December 12,
2006), to Airbus A310 Airworthiness Limitations Items Document, AI/
SE-M2/95A.0263/06, Issue 6, dated April 2006. Thereafter, except as
provided by paragraph (s) of this AD, no alternative structural
inspection intervals may be approved.
(o) Retained Exception to Issue 6 of the A310 ALI Document
This paragraph restates the requirements of paragraph (p) of AD
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). The
tolerance (grace period) for compliance with Airbus A310
Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06,
Issue 6, dated April 2006, is within 1,500 flight cycles after
January 14, 2008 (the effective date of AD 2007-25-02, Amendment 39-
15283 (72 FR 69612, December 10, 2007)), provided that none of the
following is exceeded.
(1) Thresholds or intervals in the operator's current approved
maintenance schedule that are taken from a previous ALI issue, if
existing, and are higher than or equal to those given in Airbus A310
Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06,
Issue 6, dated April 2006.
(2) 18 months after January 14, 2008 (the effective date of AD
2007-25-02, Amendment 39-15283 (72 FR 69612, December 10, 2007)).
(3) 50 percent of the intervals given in Airbus A310
Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06,
Issue 6, dated April 2006.
(4) Any application tolerance specified in Section D of Airbus
A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06,
Issue 6, dated April 2006.
(p) Retained Corrective Actions
This paragraph restates certain requirements of paragraph (q) of
AD 2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011).
Damaged, cracked, or corroded structure detected during any
inspection done in accordance with Airbus A310 Airworthiness
Limitations Items
[[Page 66776]]
Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006, must be
repaired, before further flight, in accordance with Airbus A310
Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06,
Issue 6, dated April 2006; or in accordance with other data meeting
the certification basis of the airplane that has been approved by
either the Manager, International Branch, ANM-116, or the EASA (or
its delegated agent). Where Airbus A310 Airworthiness Limitations
Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated April 2006,
specifies to contact Airbus for appropriate action: Before further
flight, repair the damaged, cracked, or corroded structure using a
method approved by either the Manager, International Branch, ANM-
116; or the EASA (or its delegated agent).
(q) Retained Reporting Requirement
This paragraph restates the requirements of paragraph (r) of AD
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). If any
damage that exceeds the allowable limits specified in Airbus A310
Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06,
Issue 6, dated April 2006, is detected during any inspection
required by this AD: At the applicable time specified in paragraph
(q)(1) or (q)(2) of this AD, submit a report of the finding to
Airbus, Customer Service Directorate, Attn: Department Manager
Maintenance Engineering, 1 Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; email: sched.maint@airbus.com. The report
must include the ALI task reference, airplane serial number, the
number of flight cycles and flight hours on the airplane,
identification of the affected structure, location and description
of the finding including its size and orientation, and the
circumstance of detection and inspection method used.
(1) If the inspection was done after January 14, 2008 (the
effective date of AD 2007-25-02, Amendment 39-15283 (72 FR 69612,
December 10, 2007)): Submit the report within 30 days after the
inspection.
(2) If the inspection was accomplished prior to January 14, 2008
(the effective date of AD 2007-25-02, Amendment 39-15283 (72 FR
69612, December 10, 2007)): Submit the report within 30 days after
January 14, 2008 (the effective date of AD 2007-25-02).
(r) Retained Revision of the ALS of the ICA
This paragraph restates the requirements of paragraph (s) of AD
2011-10-17, Amendment 39-16698 (76 FR 27875, May 13, 2011). Within 3
months after June 17, 2011 (the effective date of AD 2011-10-17):
Revise the maintenance program to incorporate the structural
inspections and inspection intervals defined in the applicable ALI
document listed in table 1 to paragraph (r) of this AD. Thereafter,
except as provided by paragraphs (u) and (s) of this AD, no
alternative structural inspections and inspection intervals may be
approved. The actions must be accomplished in accordance with the
applicable issue of the ALI. The initial ALI tasks must be done at
the times specified in the applicable ALI document listed in table 1
to paragraph (r) of this AD. Accomplishing the applicable initial
ALI tasks constitutes terminating action for the requirements of
paragraphs (g) through (q) of this AD for that airplane only. Doing
the actions required by paragraph (s) of this AD terminates the
requirements of this paragraph.
Table 1 to Paragraph (r) of This AD--Airworthiness Limitations Items Document
----------------------------------------------------------------------------------------------------------------
Model Document Issue Date
----------------------------------------------------------------------------------------------------------------
A300.............................. Airbus A300 Airworthiness Limitation 4 June 2008.
Items Document AI/SE-M2/95A.1308/07.
A310.............................. Airbus A310 Airworthiness Limitation 7 June 2008.
Items Document AI/SE[dash]M2/
95A.1309/07.
A300-600.......................... Airbus A300-600 Airworthiness 12 June 2008.
Limitation Items Document AI/
SE[dash]M2/95A.1310/07.
----------------------------------------------------------------------------------------------------------------
(s) New Maintenance Program Revision
Within 3 months after the effective date of this AD, do the
applicable revision specified in paragraph (s)(1) or (s)(2) of this
AD. The initial compliance times for the actions specified in the
documents specified in paragraphs (s)(3), (s)(4), and (s)(5) of this
AD are at the applicable compliance time specified in the document
specified in paragraphs (s)(3), (s)(4), and (s)(5) of this AD, or
within 3 months after the effective date of this AD, whichever
occurs later; except for actions identified in both documents for
the Model A300-600 series airplanes, use the applicable compliance
time specified in Airbus TR 13.1, dated February 2011, to the Airbus
A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.1310/
07, Issue 13, dated October 2010. Accomplishing the applicable
initial actions constitutes terminating action for the requirements
of paragraph (r) of this AD for that airplane only.
(1) For Model A310 series airplanes: Within 3 months after the
effective date of this AD, revise the maintenance program to
incorporate the actions (e.g., modifications and structural
inspections) and compliance times defined in Airbus A310
Airworthiness Limitation Items Document AI/SE-M2/95A.1309/07, Issue
8, dated October 2010.
(2) For Model A300-600 series airplanes: Within 3 months after
the effective date of this AD, revise the maintenance program to
incorporate the structural inspections and inspection intervals
defined in Airbus A300-600 Airworthiness Limitation Items Document
AI/SE-M2/95A.1310/07, Issue 13.1, dated February 2011.
(3) For Model A310 series airplanes: Airbus A310 Airworthiness
Limitation Items Document AI/SE-M2/95A.1309/07, Issue 8, dated
October 2010.
(4) For Model A300-600 series airplanes: Airbus A300-600
Airworthiness Limitation Items Document AI/SE-M2/95A.1310/07, Issue
13, dated October 2010.
(5) TR 13.1, dated February 2011, to the Airbus A300-600
Airworthiness Limitation Items Document AI/SE-M2/95A.1310/07, Issue
13, dated October 2010.
(t) New Alternative Inspections and Inspection Intervals Limitation
After accomplishing the revision required by paragraph (s) 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 (u) of this AD.
(u) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, 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: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425)
227-2125; 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.
(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.
(v) Related Information
Refer to MCAI EASA Airworthiness Directive 2011-0198, dated
October 19, 2011, and the service information specified in
paragraphs (v)(1) through (v)(12) of this AD, for related
information.
(1) Airbus A300 Airworthiness Limitation Items Document AI/SE-
M2/95A.1308/07, Issue 4, dated June 2008.
(2) Airbus A300 Airworthiness Limitation Items Document SEM2/
95A.1090/05, Revision 3, dated September 2005.
[[Page 66777]]
(3) Airbus A300-600 Airworthiness Limitation Items Document AI/
SE-M2/95A.0502/06, Revision 11, dated April 2006.
(4) Airbus A300-600 Airworthiness Limitation Items Document AI/
SE-M2/95A.1310/07, Issue 13, dated October 2010.
(5) Airbus A300-600 Airworthiness Limitation Items Document AI/
SE-M2/95A.1310/07, Revision 12, dated June 2008.
(6) Airbus A310 Airworthiness Limitation Items Document AI/SE-
M2/95A.1309/07, Issue 8, dated October 2010.
(7) Airbus A310 Airworthiness Limitation Items Document AI/SE-
M2/95A.1309/07, Revision 7, dated June 2008.
(8) Airbus A310 Airworthiness Limitations Items Document AI/SE-
M2/95A.0263/06, Revision 6, dated April 2006.
(9) Airbus Industrie A300 Structural Inspection Document,
Revision 2, dated June 1994.
(10) Airbus Temporary Revision 13.1, dated February 2011, to
Airbus A300-600 Airworthiness Limitation Items Document AI/SE-M2/
95A.1310/07, Revision 13, dated October 2010.
(11) Airbus Temporary Revision 3.1, dated April 2006, including
attachment, dated April 2006, and including attachments dated
September 2005, to Airbus A300 Airworthiness Limitation Items,
Document SEM2/95A.1090/05, Issue 3, dated September 2005.
(12) Airbus Temporary Revision 6.1, including pages 1 and 2 of
Section D and page 1 of Section E, dated November 2006, to Airbus
A310 Airworthiness Limitations Items Document, AI/SE-M2/95A.0263/06,
Issue 6, dated April 2006.
Issued in Renton, Washington, on October 30, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2012-27126 Filed 11-6-12; 8:45 am]
BILLING CODE 4910-13-P
