[Federal Register Volume 76, Number 16 (Tuesday, January 25, 2011)]
[Proposed Rules]
[Pages 4260-4263]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-1439]



[[Page 4260]]

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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]
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), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede three existing ADs. This 
proposed 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. The proposed AD would require actions that 
are intended to address the unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by March 11, 2011.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-40, 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; e-mail [email protected]; Internet http://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 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 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, FAA, Transport Airplane Directorate, 
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-2011-0030; 
Directorate Identifier 2009-NM-183-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 http://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 February 6, 2007, we issued AD 2007-04-11, Amendment 39-14943 
(72 FR 8604, February 27, 2007). That AD required actions intended to 
address an unsafe condition on Airbus Model A300 B2 and B4 series 
airplanes.
    On September 19, 2007, we issued AD 2007-20-03, Amendment 39-15213 
(72 FR 54536, September 26, 2007). That AD required actions intended to 
address an unsafe condition on Airbus Model A300-600 series airplanes.
    On November 23, 2007, we issued AD 2007-25-02, Amendment 39-15283 
(72 FR 69612, December 10, 2007). That AD required actions intended to 
address an unsafe condition on Airbus Model A310 series airplanes.
    Since we issued ADs 2007-04-11, 2007-20-03, and 2007-25-02, we have 
determined that the airworthiness limitations for these airplanes must 
be updated in order to adequately address the unsafe condition. The 
European Aviation Safety Agency (EASA), which is the Technical Agent 
for the Member States of the European Community, has issued EASA 
Airworthiness Directive 2009-0155, dated July 17, 2009 (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 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

[[Page 4261]]

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.

Relevant Service Information

    Airbus has issued A300-600 Airworthiness Limitation Items (ALI) 
Document AI/SE-M2/95A.1310/07, Issue 12, dated June 2008; A300 ALI 
Document AI/SE-M2/95A.1308/07, Issue 4, dated June 2008; and A310 ALI 
Document, AI/SE-M2/95A.1309/07, Issue 7, dated June 2008. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

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 proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would 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 would take about 1 work-hour per product to 
comply with the new 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 $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 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

    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 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:

Airbus: Docket No. FAA-2011-0030; Directorate Identifier 2009-NM-
183-AD.

Comments Due Date

    (a) We must receive comments by March 11, 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

[[Page 4262]]

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'' (SSID), Revision 2, dated June 1994 
(``Revision 2 of the SSID''). Accomplish the actions specified in 
the service bulletins identified in Section 6, ``SB Reference 
List,'' Revision 2 of the SSID, 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,'' Revision 2 of the SSID: Accomplish the actions specified in 
those service bulletins within the grace period specified in that 
service bulletin. 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,'' Revision 2 of the SSID, 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 (ALI) Document SEM2/95A.1090/05, 
Issue 3, dated September 2005, as revised by Airbus A300 Temporary 
Revision (TR) 3.1, dated April 2006 (``Issue 3 of the ALI''). 
Accomplish the actions specified in Issue 3 of the ALI at the times 
specified in that ALI, except as provided by paragraph (i) of this 
AD. The actions must be accomplished in accordance with Issue 3 of 
the ALI. 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 (``Issue 3 of the ALI''), 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 Issue 3 of the ALI: 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 A300Airworthiness 
Limitation Items Document SEM2/95A.1090/05, Issue 3, dated September 
2005 (``Issue 3 of the ALI''), must be repaired, before further 
flight, in accordance with Issue 3 of the ALI, 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; or by the European Aviation Safety 
Agency (EASA) (or its delegated agent).
    (k) Where the Airbus A300Airworthiness 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 (ALI) Document AI/SE-M2/95A.0502/06, Issue 11, 
dated April 2006 (``Issue 11 of the ALI''). The tolerance (grace 
period) for compliance (specified in paragraph 2 of Section B--
Program Rules) with Issue 11 of the ALI 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 Issue 11 of 
the ALI.
    (2) 8 months after October 31, 2007.
    (3) 50 percent of the intervals given in Issue 11 of the ALI.
    (4) Any application tolerance given in the task description of 
Issue 11 of the ALI.

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 (ALI) Document, AI/SE-M2/95A.0263/
06, Issue 6, dated April 2006 (approved by the European Aviation 
Safety Agency (EASA) on May 31, 2006). Accomplish the actions 
specified in Issue 6 of the ALI at the times specified in that ALI, 
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 Issue 6 of the ALI must be accomplished in 
accordance with Issue 6 of the ALI.
    (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 Issue 6 of the ALI. Thereafter, 
except as provided by paragraph

[[Page 4263]]

(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 (ALI) Document, AI/SE-M2/95A.0263/
06, Issue 6, dated April 2006 (``Issue 6 of the ALI''), 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 Issue 6 of 
the ALI.
    (2) 18 months after January 14, 2008.
    (3) 50 percent of the intervals given in Issue 6 of the ALI.
    (4) Any application tolerance specified in Section D of Issue 6 
of the ALI.

Corrective Actions

    (q) Damaged, cracked, or corroded structure detected during any 
inspection done in accordance with Airbus A310 Airworthiness 
Limitation Items (ALI) Document, AI/SE-M2/95A.0263/06, Issue 6, 
dated April 2006 (``Issue 6 of the ALI''), must be repaired, before 
further flight, in accordance with Issue 6 of the ALI; 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, Transport Airplane Directorate, FAA, or the EASA 
(or its delegated agent). Where Issue 6 of the ALI 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 (ALI) 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 ALS of the ICA 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.

                                Table 1--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.
----------------------------------------------------------------------------------------------------------------

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 the 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. Send information 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. 
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 (ALI) 
Document AI/SE-M2/95A.0502/06, Issue 11, dated April 2006; Airbus 
A300-600 ALI Document AI/SE-M2/95A.1310/07, Issue 12, dated June 
2008; Airbus A300 ALI Document SEM2/95A.1090/05, Issue 3, dated 
September 2005, as revised by Airbus A300 Temporary Revision (TR) 
3.1, dated April 2006; Airbus A300 ALI Document AI/SE-M2/95A.1308/
07, Issue 4, dated June 2008; Airbus A310 ALI Document, AI/SE-M2/
95A.0263/06, Issue 6, dated April 2006; Airbus TR 6.1, dated 
November 2006; Airbus A310 ALI Document, AI/SE-M2/95A.1309/07, Issue 
7, dated June 2008; and Airbus Industrie A300 Structural Inspection 
Document'' (SSID), Revision 2, dated June 1994; for related 
information.

    Issued in Renton, Washington, on January 13, 2011.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-1439 Filed 1-24-11; 8:45 am]
BILLING CODE 4910-13-P