[Federal Register Volume 76, Number 93 (Friday, May 13, 2011)]
[Rules and Regulations]
[Pages 27875-27880]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-11333]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0030; Directorate Identifier 2009-NM-183-AD;
Amendment 39-16698; AD 2011-10-17]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300 and A310 Series
Airplanes, and Model A300 B4-600, B4-600R, and F4-600R Series
Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called
A300-600 Series Airplanes)
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding three existing airworthiness directives
(ADs) that apply to the products listed above. This AD results from
mandatory continuing airworthiness information (MCAI) originated by an
aviation authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
The airworthiness limitations applicable to the Damage Tolerant
Airworthiness Limitation Items (DT ALI) are currently listed in
Airbus ALI Documents, which are referenced in the A300, A310, and
A300-600 Airworthiness Limitations Section (ALS) Part 2. Airbus has
recently revised the ALI Documents, which have been approved by the
European Aviation Safety Agency (EASA).
* * * * *
The actions contained in these revised documents, which
introduce more restrictive maintenance requirements and/or
airworthiness limitations, have been identified as mandatory actions
for continued airworthiness. * * *
The unsafe condition is fatigue cracking, damage, or corrosion in
principal structural elements, which could result in reduced structural
integrity of the airplane. We are issuing this AD to require actions to
correct the unsafe condition on these products.
DATES: This AD becomes effective June 17, 2011.
The Director of the Federal Register approved the incorporation by
reference
[[Page 27876]]
of certain publications listed in this AD as of June 17, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of January
14, 2008 (72 FR 69612, December 10, 2007).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
October 31, 2007 (72 FR 54536, September 26, 2007).
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of April
3, 2007 (72 FR 8604, February 27, 2007).
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of August
9, 1996 (61 FR 35122, July 5, 1996).
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on January 25, 2011 (76
FR 4260), and proposed to supersede 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). That NPRM proposed to correct an
unsafe condition for the specified products. The MCAI states:
The airworthiness limitations applicable to the Damage Tolerant
Airworthiness Limitation Items (DT ALI) are currently listed in
Airbus ALI Documents, which are referenced in the A300, A310, and
A300-600 Airworthiness Limitations Section (ALS) Part 2. Airbus has
recently revised the ALI Documents, which have been approved by the
European Aviation Safety Agency (EASA).
--Airbus A300 ALI Document issue 04.
--Airbus A310 ALI Document issue 07 and
--Airbus A300-600 ALI Document issue 12
The actions contained in these revised documents, which
introduce more restrictive maintenance requirements and/or
airworthiness limitations, have been identified as mandatory actions
for continued airworthiness. EASA issued ADs 2006-0071, 2006-0260,
and 2006-0374 [which correspond to FAA ADs 2007-04-11, 2007-25-02,
and 2007-20-03] to require compliance with the maintenance
requirements and associated airworthiness limitations defined in
previous issues of these Airbus ALI documents.
For the reason described above, [the] EASA AD supersedes
existing ADs 2006-0071, 2006-0260, and 2006-0374 and requires an
update to the approved aircraft maintenance programme and compliance
with the maintenance requirements and associated airworthiness
limitations defined in the Airbus ALI Documents listed above.
The unsafe condition is fatigue cracking, damage, or corrosion in
principal structural elements, which could result in reduced structural
integrity of the airplane. The required actions include revising the
Airworthiness Limitations section of the Instructions for Continued
Airworthiness to incorporate new and revised structural inspections and
inspection intervals. You may obtain further information by examining
the MCAI in the AD docket.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow our FAA policies. Any such differences
are highlighted in a NOTE within the AD.
Costs of Compliance
We estimate that this AD will affect about 206 products of U.S.
registry.
The actions that are required by AD 2007-04-11, AD 2007-20-03, and
AD 2007-25-02, and retained in this proposed AD, take about 1 work hour
per product. The average labor rate is $85 per work-hour. Based on
these figures, we estimate the cost of those actions on U.S. operators
to be $85 per product.
We estimate that it will take about 1 work-hour per product to
comply with the new basic requirements of this AD. The average labor
rate is $85 per work-hour. Based on these figures, we estimate the cost
of this AD to the U.S. operators to be $17,510, 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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); 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 AD and placed it in the AD docket.
[[Page 27877]]
Examining the AD Docket
You may examine the AD docket on the Internet at http://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 the NPRM, 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-14943 (72 FR
8604, February 27, 2007); Amendment 39-15213 (72 FR 54536, September
26, 2007); and Amendment 39-15283 (72 FR 69612, December 10, 2007); and
adding the following new AD:
2011-10-17 Airbus: Amendment 39-16698. Docket No. FAA-2011-0030;
Directorate Identifier 2009-NM-183-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective June 17,
2011.
Affected ADs
(b) This AD supersedes AD 2007-04-11, Amendment 39-14943; AD
2007-20-03, Amendment 39-15213; and AD 2007-25-02, Amendment 39-
15283.
Applicability
(c) 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) Models A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-
622R, F4-605R, and F4-622R airplanes, and Model A300 C4-605R Variant
F airplanes.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new inspections. Compliance with
these inspections is required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered, or repaired in the
areas addressed by these inspections, the operator may not be able
to accomplish the inspections described in the revisions. In this
situation, to comply with 14 CFR 91.403(c), the operator must
request approval for an alternative method of compliance according
to paragraph (t)(1) of this AD. The request should include a
description of changes to the required inspections that will ensure
the continued damage tolerance of the affected structure. The FAA
has provided guidance for this determination in Advisory Circular
(AC) 25-1529-1.
Subject
(d) Air Transport Association (ATA) of America Codes 52: Doors;
53: Fuselage; 54: Nacelles/pylons; 55: Stabilizers; 57: Wings; and
71: Powerplant (for Model A300-600 only).
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
The airworthiness limitations applicable to the Damage Tolerant
Airworthiness Limitation Items (DT ALI) are currently listed in
Airbus ALI Documents, which are referenced in the A300, A310, and
A300-600 Airworthiness Limitations Section (ALS) Part 2. Airbus has
recently revised the ALI Documents, which have been approved by the
European Aviation Safety Agency (EASA).
* * * * *
The actions contained in these revised documents, which
introduce more restrictive maintenance requirements and/or
airworthiness limitations, have been identified as mandatory actions
for continued airworthiness. * * *
The unsafe condition is fatigue cracking, damage, or corrosion in
principal structural elements, which could result in reduced
structural integrity of the airplane.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Certain Requirements of AD 2007-04-11
(g) Within one year after August 9, 1996 (the effective date of
AD 96-13-11), 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 (s) 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.
(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.
Revision of the Maintenance Inspection Program
(h) 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), 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 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 (i) 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 (s) of
this AD terminates the actions required by this paragraph.
(i) 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.
Corrective Actions
(j) 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,
[[Page 27878]]
dated April 2006, except as provided by paragraph (k) 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).
(k) 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).
No Fleet Sampling
(l) 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.
No Reporting
(m) 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.
Restatement of Requirements of AD 2007-20-03
Actions and Compliance
(n) For airplanes identified in paragraph (c)(3) of this AD:
Within 3 months after October 31, 2007 (the effective date AD 2007-
20-03), revise the ALS of the Instructions for Continued
Airworthiness 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, provided that none of the following is exceeded.
Accomplishing the initial ALI tasks required by paragraph (s) 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.
(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.
Restatement of Requirements of AD 2007-25-02
Revision of the Airworthiness Limitations Section (ALS) of the
Instructions for Continued Airworthiness (ICA)
(o) 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), do the actions specified in paragraphs (o)(1) and
(o)(2) of this AD. Accomplishing the initial ALI tasks required by
paragraph (s) 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 (p) of this AD.
Thereafter, except as provided by paragraphs (o)(2) and (t)(1) 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
Temporary Revision (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 (t)(1) of this AD, no
alternative structural inspection intervals may be approved.
Exception to Issue 6 of the ALI
(p) 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, 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.
(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.
Corrective Actions
(q) Damaged, cracked, or corroded structure detected during any
inspection done in accordance with Airbus A310 Airworthiness
Limitations Items 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).
Reporting Requirement
(r) 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 (r)(1) or (r)(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; e-mail: [email protected]. 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: Submit
the report within 30 days after the inspection.
(2) If the inspection was accomplished prior to January 14,
2008: Submit the report within 30 days after January 14, 2008.
New Requirements of This AD
Revision of the ALS of the Instructions for ICA
(s) Within 3 months after the effective date of this AD: Revise
the maintenance program to incorporate the structural inspections
and inspection intervals defined in the applicable ALI document
listed in Table 1 of this AD. Thereafter, except as provided by
paragraph (t)(1) 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 of this AD. Accomplishing
the applicable initial ALI tasks constitutes terminating action for
the requirements of paragraphs (g) through (r) of this AD for that
airplane only.
[[Page 27879]]
Table 1--Airworthiness Limitations Items Document
----------------------------------------------------------------------------------------------------------------
Model Document Issue Date
----------------------------------------------------------------------------------------------------------------
A300................................... Airbus A300 Airworthiness 4 June 2008.
Limitation Items Document AI/
SE-M2/95A.1308/07.
A310................................... Airbus A310 Airworthiness 7 June 2008.
Limitation Items Document AI/
SE-M2/95A.1309/07.
A300-600............................... Airbus A300-600 Airworthiness 12 June 2008.
Limitation Items Document AI/
SE-M2/95A.1310/07.
----------------------------------------------------------------------------------------------------------------
FAA AD Differences
Note 2: This AD differs from the MCAI and/or service
information as follows:
Where the MCAI includes a compliance time of ``from the
effective date of this AD,'' we have determined that a compliance
time of ``within 3 months after the effective date of this AD'' is
appropriate. The manufacturer and EASA agree with this difference in
compliance time.
Other FAA AD Provisions
(t) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Dan Rodina,
Aerospace Engineer, International Branch, ANM-116, FAA, Transport
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 227-2125; fax (425) 227-1149.
Information may be e-mailed to: [email protected].
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 2007-04-11,
Amendment 39-14943; AD 2007-20-03, Amendment 39-15213; and AD 2007-
25-02, Amendment 39-15283; as applicable; are approved as AMOCs for
the corresponding provisions of 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.
(3) Reporting Requirements: A federal agency may not conduct or
sponsor, and a person is not required to respond to, nor shall a
person be subject to a penalty for failure to comply with a
collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 5
minutes per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.,
SW., Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
Related Information
(u) Refer to MCAI EASA Airworthiness Directive 2009-0155, dated
July 17, 2009; Airbus A300-600 Airworthiness Limitation Items
Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006; Airbus
A300-600 Airworthiness Limitation Items Document AI/SE-M2/95A.1310/
07, Issue 12, dated June 2008; Airbus A300 Airworthiness Limitation
Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, as
revised by Airbus A300 Temporary Revision 3.1, dated April 2006;
Airbus A300 Airworthiness Limitation Items Document AI/SE-M2/
95A.1308/07, Issue 4, dated June 2008; Airbus A310 Airworthiness
Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated
April 2006; Airbus Temporary Revision 6.1, dated November 2006;
Airbus A310 Airworthiness Limitation Items Document, AI/SE-M2/
95A.1309/07, Issue 7, dated June 2008; and Airbus Industrie A300
Structural Inspection Document, Revision 2, dated June 1994; for
related information.
Material Incorporated by Reference
(v) You must use the service information contained in Table 2 of
this AD to do the actions required by this AD, as applicable, unless
the AD specifies otherwise.
Table 2--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Issue/revision Date
----------------------------------------------------------------------------------------------------------------
Airbus A300 Airworthiness Limitation 4.................................... June 2008.
Items Document AI/SE-M2/95A.1308/07.
Airbus A300 Airworthiness Limitation 3.................................... September 2005.
Items Document SEM2/95A.1090/05, as
revised by Airbus A300 TR 3.1, dated
April 2006.
Airbus A300 Airworthiness Limitation Original............................. April 2006.
Items, Document SEM2/95A.1090/05,
Temporary Revision 3.1, including
attachment, dated April 2006, and
including attachments dated September
2005.
Airbus Temporary Revision 6.1, Original............................. November 2006.
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.
Airbus A310 Airworthiness Limitation 7.................................... June 2008.
Items Document AI/SE[dash]M2/95A.1309/
07.
Airbus A310 Airworthiness Limitations 6.................................... April 2006.
Items Document AI/SE[dash]M2/95A.0263/
06.
Airbus A300-600 Airworthiness 12................................... June 2008.
Limitation Items Document AI/
SE[dash]M2/95A.1310/07.
Airbus A300-600 Airworthiness 11................................... April 2006.
Limitation Items Document AI/
SE[dash]M2/95A.0502/06.
Airbus Industrie A300 Structural 2.................................... June 1994.
Inspection Document.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the service information contained in
Table 3 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.
[[Page 27880]]
Table 3--New Material Incorporated by Reference
------------------------------------------------------------------------
Document Issue Date
------------------------------------------------------------------------
Airbus A300 Airworthiness Limitation 4 June 2008.
Items Document AI/SE-M2/95A.1308/07.
Airbus A310 Airworthiness Limitation 7 June 2008.
Items Document AI/SE-M2/95A.1309/07.
Airbus A300-600 Airworthiness 12 June 2008.
Limitation Items Document AI/SE-M2/
95A.1310/07.
------------------------------------------------------------------------
(2) The Director of the Federal Register previously approved
the incorporation by reference of Airbus A310 Airworthiness
Limitations Items Document, AI/SE-M2/95A.0263/06, Issue 6, dated
April 2006; and 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; on January 14, 2008 (72 FR
69612, December 10, 2007).
(3) The Director of the Federal Register previously approved the
incorporation by reference of Airbus A300-600 Airworthiness
Limitation Items Document AI/SE-M2/95A.0502/06, Issue 11, dated
April 2006, on October 31, 2007 (72 FR 54536, September 26, 2007).
(4) The Director of the Federal Register previously approved the
incorporation by reference of Airbus A300 Airworthiness Limitations
Items Document SEM2/95A.1090/05, Issue 3, dated September 2005, as
revised by Airbus A300 Airworthiness Limitation Items Document SEM2/
95A.1090/05, Temporary Revision 3.1, including attachment, dated
April 2006, and including attachments, dated September 2005, on
April 3, 2007 (72 FR 8604, February 27, 2007).
(5) The Director of the Federal Register previously approved the
incorporation by reference of Airbus Industrie A300 Supplemental
Structural Inspection Document, Revision 2, dated June 1994, on
August 9, 1996 (61 FR 35122, July 5, 1996).
(6) For service information identified in this 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; e-mail [email protected];
Internet http://www.airbus.com.
(7) You may review copies of the 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.
(8) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on May 2, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-11333 Filed 5-12-11; 8:45 am]
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