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[Federal Register: March 11, 2010 (Volume 75, Number 47)]
[Rules and Regulations]               
[Page 11428-11433]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr11mr10-3]                         

-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0789; Directorate Identifier 2008-NM-185-AD; 
Amendment 39-16228; AD 2010-06-04]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A300 B2-1C, B2-203, B2K-
3C, B4-103, B4-203, B4-2C Airplanes; Model A310 Series Airplanes; and 
Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, and B4-622R 
Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for 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:

    Cracks have been found on pylon side panels (upper section) at 
rib 8 on Airbus A300, A310 and A300-600 aircraft equipped with 
General Electric engines. Investigation of these findings indicates 
that this problem is likely to affect aircraft of this type design 
with other engine installations. This condition, if not corrected, 
can lead to reduced strength [structural integrity] of the pylon 
primary structure.
* * * * *
    The unsafe condition is reduced structural integrity of the pylon 
primary structure, which could cause detachment of the engine from the 
fuselage. We are issuing this AD to require actions to correct the 
unsafe condition on these products.

DATES: This AD becomes effective April 15, 2010.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of April 15, 
2010.

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, Transport Airplane Directorate, FAA, 
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 September 21, 2009 
(74 FR 48024). That NPRM proposed to correct an unsafe condition for 
the specified products. The MCAI states:

    Cracks have been found on pylon side panels (upper section) at 
rib 8 on Airbus A300, A310 and A300-600 aircraft equipped with 
General Electric engines. Investigation of these findings indicates 
that this problem is likely to affect aircraft of this type design 
with other engine installations. This condition, if not corrected, 
can lead to reduced strength [structural integrity] of the pylon 
primary structure.
    In order to detect any crack propagation at an early stage, thus 
avoiding an extensive repair, Airbus issued Service Bulletins (SB) 
A300-54-0075, A310-54-2018 and A300-54-6015. * * *
    This AD requires the implementation of this * * * inspection 
programme.

    The unsafe condition is reduced structural integrity of the pylon 
primary structure, which could cause detachment of the engine from the 
fuselage. Required actions include repetitive detailed visual 
inspections, or repetitive eddy current and detailed visual 
inspections, to detect cracks, depending on the airplane configuration, 
and corrective actions if necessary. The corrective actions include 
repairing the cracking, and contacting Airbus for repair instructions 
and doing the repair, as applicable. 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 considered the comments received.

Request To Clarify Reporting Requirement

    American Airlines requests that we remove the requirement for 
reporting findings to Airbus. The commenter states that Appendix 1, 2, 
and 3 in Airbus Service Bulletin A300-54-6015 require findings to be 
reported; however, the proposed rule specifically excludes Appendix 1, 
2, and 3 in Table 2 of this AD. American Airlines states the difference 
is not addressed in the proposed rule. The commenter also states that 
reporting findings within a specified time period has no effect on 
improving safety and should not be mandated by the proposed rule.
    We agree that reporting inspection findings to Airbus is not 
necessary in this AD for the reasons stated by the commenter. Since the 
MCAI requires reporting inspection findings to Airbus and it is not our 
intent to require those reports, we have added Note 2 in this AD to 
clarify that this AD does not include a reporting requirement.

Request To Refer to Paragraph 3.B. in Airbus Mandatory Service Bulletin 
A300-54-6015, Revision 02, Dated June 26, 2008, for Inspection Task

    The commenter, R. L. Vernon, requests that paragraph (f)(1) of the 
NPRM refer to paragraph 3.B. of Airbus Mandatory Service Bulletin A300-
54-6015, Revision 02, dated June 26, 2008, rather than paragraph 3.E., 
for the inspection task. The commenter states

[[Page 11429]]

that paragraph 3.E. incorrectly calls for the access panels to be 
removed, rather than installed.
    We concur with the request to refer to paragraph 3.B of Airbus 
Mandatory Service Bulletin A300-54-6015, Revision 02, dated June 26, 
2008. It appears there is a typographical error in paragraph 3.E. of 
Airbus Mandatory Service Bulletin A300-54-6015, Revision 02, dated June 
26, 2008, which instructs operators to remove access panels rather than 
to install access panels. We have revised paragraph (f) of this AD to 
refer to the specific section of the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A300-54-6015, Revision 02, dated June 
26, 2008, for that action. We have also revised paragraphs (f)(4) and 
(f)(7) of this AD to refer to paragraph 3.C. rather than paragraph 3.B. 
of the Accomplishment Instructions.

Request To Extend Grace Period

    FedEx requests that the grace period for the inspection to detect 
cracking be extended from 250 flight cycles to 350 flight cycles. FedEx 
states the inspection threshold/grace periods do not fit into their 
planned scheduled maintenance checks. FedEx states that 61 of 95 
affected airplanes have exceeded the AD compliance threshold, and thus 
will be subject to the grace period of 250 flight cycles. FedEx states 
that the grace period of 250 flight cycles does not allow all airplanes 
to be inspected at a B-check (every 500 flight hours), thereby 
requiring the airplanes to be inspected at a special visit.
    We do not agree with the request to extend the grace period. An 
extension to the grace period cannot be provided easily and depends on 
the airplane and structure configuration, as well as the number of 
flight cycles and flight hours accumulated from repair embodiment or 
from first flight. Under the provisions of paragraph (g)(1) of the 
final rule, we will consider requests for approval of an extension of 
the grace period if sufficient data are submitted to substantiate that 
the new grace period would provide an acceptable level of safety. We 
have not changed the AD in this regard.

Request for Clarification of Table 1 of the NPRM

    FedEx requests that the compliance times listed in Table 1 of the 
NPRM be written more clearly. FedEx states that the 18,000-flight-cycle 
criterion appears to be arbitrary and adds confusion for the reader. 
FedEx provides an example that excludes the criterion of 18,000 flight 
cycles.
    We disagree with the request to change Table 1 of the NPRM. The 
thresholds specified in the second column of that table were derived 
from the note in the Configuration 01 table in paragraph 1.E.(2) of 
Airbus Service Bulletin A300-54-6015, Revision 02, dated June 26, 2008. 
The note states that the inspection is to be done within 2,000 flight 
cycles without exceeding 20,000 total flight cycles/40,000 total flight 
hours from first flight. The compliance times specified in Table 1 of 
this AD reflect the intent of Airbus Mandatory Service Bulletin A300-
54-6015, Revision 02, dated June 26, 2008. We have not changed the AD 
in this regard.

Conclusion

    We reviewed the available data, including the comments received, 
and determined that air safety and the public interest require adopting 
the AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

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.

Explanation of Change of Costs of Compliance

    Since issuance of the original NPRM, we have increased the labor 
rate used in the Costs of Compliance from $80 per work-hour to $85 per 
work-hour. The Costs of Compliance information, below, reflects this 
increase in the specified hourly labor rate.

Costs of Compliance

    We estimate that this AD will affect 230 products of U.S. registry. 
We also estimate that it will take about 4 work-hours per product to 
comply with the 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 $78,200, or $340 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.

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.

[[Page 11430]]

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

0
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 adding the following new AD:

2010-06-04 Airbus: Amendment 39-16228. Docket No. FAA-2009-0789; 
Directorate Identifier 2008-NM-185-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective April 
15, 2010.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to the airplanes, certificated in any 
category, identified in paragraphs (c)(1), (c)(2), and (c)(3) of 
this AD.
    (1) Airbus Model A300 B2-1C, A300 B2-203, A300 B2K-3C, A300 B4-
103, A300 B4-203, and A300 B4-2C airplanes, all serial numbers 
incorporating Airbus Modification 02434 or 03599;
    (2) Airbus Model A310-203, A310-204, A310-221, A310-222, A310-
304, A310-322, A310-324, and A310-325 airplanes, all serial numbers, 
except airplanes incorporating Airbus Modification 10432;
    (3) Airbus Model A300 B4-601, A300 B4-603, A300 B4-605R, A300 
B4-620, A300 B4-622, and A300 B4-622R airplanes, all serial numbers, 
except airplanes incorporating Airbus Modification 10432.

Subject

    (d) Air Transport Association (ATA) of America Code 54: 
Nacelles/Pylons.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    ``Cracks have been found on pylon side panels (upper section) at 
rib 8 on Airbus A300, A310 and A300-600 aircraft equipped with 
General Electric engines. Investigation of these findings indicates 
that this problem is likely to affect aircraft of this type design 
with other engine installations. This condition, if not corrected, 
can lead to reduced strength [structural integrity] of the pylon 
primary structure.
    ``In order to detect any crack propagation at an early stage, 
thus avoiding an extensive repair, Airbus issued Service Bulletins 
(SB) A300-54-0075, A310-54-2018 and A300-54-6015. * * *
    ``This AD requires the implementation of this * * * inspection 
programme.''

    The unsafe condition is reduced structural integrity of the 
pylon primary structure, which could cause detachment of the engine 
from the fuselage. Required actions include repetitive detailed 
visual inspections, or repetitive eddy current and detailed visual 
inspections, to detect cracks, depending on the airplane 
configuration, and corrective actions if necessary. The corrective 
actions include repairing the cracking, and contacting Airbus for 
repair instructions and doing the repair, as applicable.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) For Configuration 01 airplanes as identified in the 
applicable service bulletin identified in Table 2 of this AD: At the 
applicable time specified in Table 1 of this AD, except as required 
by paragraphs (f)(2) and (f)(3) of this AD, perform a detailed 
visual inspection of the pylons 1 and 2 side panels (upper section) 
at rib 8, in accordance with paragraph 3.B. of the Accomplishment 
Instructions of the applicable service bulletin identified in Table 
2 of this AD. Repeat the inspection at the time specified in Table 1 
of this AD.

                                  Table 1--Compliance Times for Configuration 1
----------------------------------------------------------------------------------------------------------------
                                                              Whichever occurs later
                                                     ----------------------------------------   And repeat the
           For model--                 That have      Inspect before the                         inspection at
                                     accumulated--     accumulation of--      Or within--      intervals not to
                                                                                                   exceed--
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2-203, and B2K-3C    17,500 total       20,000 total        250 flight          4,300 flight
 airplanes.                        flight.\1\.         flight cycles or    cycles.\2\.         cycles.
                                                       40,000 total
                                                       flight hours,
                                                       whichever occurs
                                                       first.
A300 B4-103, B4-203, and B4-2C    18,000 total       20,000 total        250 flight          4,300 flight
 airplanes.                        flight cycles.\1\.  flight cycles or    cycles.\2\.         cycles.
                                                       40,000 total
                                                       flight hours,
                                                       whichever occurs
                                                       first.
A300 B4-601, B4-603, B4-605R, B4- 18,000 total       20,000 total        250 flight          3,600 flight
 620, B4-622, and B4-622R          flight cycles.\1\.  flight cycles or    cycles.\2\.         cycles.
 airplanes.                                            40,000 total
                                                       flight hours,
                                                       whichever occurs
                                                       first.
A310-200 airplanes with GE CF6-   18,000 total       19,500 total        250 flight          6,700 flight
 80A3 or Pratt & Whitney engines.  flight cycles.\1\.  flight cycles or    cycles.\2\.         cycles or 13,400
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-200 airplanes with GE CF6-   18,000 total       19,500 total        250 flight          5,800 flight
 80C2 engines.                     flight cycles.\1\.  flight cycles or    cycles.\2\.         cycles or 11,600
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-300 SR \3\ airplanes with    18,000 total       19,500 total        250 flight          6,700 flight
 Pratt & Whitney JT9D engines.     flight cycles.\1\.  flight cycles or    cycles.\2\.         cycles or 18,700
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-300 SR \3\ airplanes with    18,000 total       19,500 total        250 flight          5,700 flight
 GE engines.                       flight cycles.\1\.  flight cycles or    cycles.\2\.         cycles or 15,900
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-300 SR \3\ airplanes with    18,000 total       19,500 total        250 flight          5,800 flight
 Pratt & Whitney 4000 engines.     flight cycles.\1\.  flight cycles or    cycles.\2\.         cycles or 16,200
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-300 LR \4\ airplanes with    18,000 total       19,500 total        250 flight          6,000 flight
 Pratt & Whitney JT9D engines.     flight cycles.\1\.  flight cycles or    cycles.\2\.         cycles or 30,300
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-300 LR \4\ airplanes with    18,000 total       19,500 total        250 flight          5,100 flight
 GE engines.                       flight cycles.\1\.  flight cycles or    cycles.\2\.         cycles or 25,500
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
A310-300 LR \4\ airplanes with    18,000 total       19,500 total        250 flight          5,200 flight
 Pratt & Whitney 4000 engines.     flight cycles.\1\.  flight cycles or    cycles.\2\.         cycles or 26,300
                                                       55,500 total                            flight hours,
                                                       flight hours,                           whichever occurs
                                                       whichever occurs                        first.
                                                       first.
----------------------------------------------------------------------------------------------------------------
\1\ As of the effective date of this AD.
\2\ After the effective date of this AD.
\3\ ``SR'' applies to airplanes with average flights less than 4 flight hours.
\4\ ``LR'' refers to airplanes with average flights of 4 or more flight hours.

    (2) For Model A300 and A300-600 airplanes that have accumulated 
more than 40,000 total flight hours as of the effective date of this 
AD: Within 250 flight cycles after the effective date of this AD, do 
the actions specified in paragraph (f)(1) of this AD.
    (3) For Model A310 airplanes that have accumulated more than 
55,500 total flight hours as of the effective date of this AD: 
Within 250 flight cycles after the effective date of this AD, do the 
actions specified in paragraph (f)(1) of this AD.
    (4) For Configuration 01 airplanes, as identified in the 
applicable service bulletin identified in Table 2 of this AD: If a 
crack is found during any inspection required by this AD, before 
further flight, install a doubler, in accordance with paragraph 3.C. 
of the Accomplishment Instructions of the applicable service 
bulletin identified in Table 2 of this AD.
    (5) For Configuration 02 airplanes, as identified in the 
applicable service bulletin identified in Table 2 of this AD: At the 
applicable time specified in paragraph 1.E.(2) of the applicable 
service bulletin identified in Table 2 of this AD, or within 250 
flight cycles after the effective date of this AD, whichever occurs 
later, perform a detailed visual inspection of the pylons 1 and 2 
side panels (upper section) at rib 8, in accordance with paragraph 
3.B. of the Accomplishment Instructions of the applicable service 
bulletin identified in Table 2 of this AD.
    (6) For Configuration 03 airplanes, as identified in the 
applicable service bulletin identified in Table 2 of this AD: At the 
applicable time specified in paragraph 1.E.(2) of the applicable 
service bulletin identified in Table 2 of this AD, or within 250 
flight cycles after the effective date of this AD, whichever occurs 
later, perform a detailed visual inspection, and a high frequency 
eddy current inspection as applicable, of the pylons 1 and 2 side 
panels (upper section) at rib 8, in accordance with paragraph 3.B. 
of the Accomplishment Instructions of the

[[Page 11432]]

applicable service bulletin identified in Table 2 of this AD.
    (7) For Configuration 02 and 03 airplanes, as identified in the 
applicable service bulletin identified in Table 2 of this AD: If a 
crack is found during any inspection required by paragraph (f)(1), 
(f)(5), or (f)(6) of this AD, before further flight, repair in 
accordance with paragraph 3.C. of the Accomplishment Instructions of 
the applicable service bulletin identified in Table 2 of this AD.
    (8) For all airplanes, except those in Configuration 01, as 
identified in the applicable service bulletin identified in Table 2 
of this AD: Repeat the inspection specified in paragraph (f)(1), 
(f)(5), or (f)(6) of this AD, as applicable, at the intervals 
specified in paragraph 1.E.(2) of the applicable service bulletin 
identified in Table 2 of this AD.

                                           Table 2--Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                         Use Airbus Mandatory Service
              For model--                         Bulletin--            Revision--             Dated--
----------------------------------------------------------------------------------------------------------------
A300 B2-1C, B2-203, B2K-3C, B4-103, B4- A300-54-0075, excluding                 02  June 26, 2008.
 203, and B4-2C airplanes                Appendices 1, 2, and 3.
A300 B4-601, B4-603, B4-605R, B4-620,   A300-54-6015, excluding                 02  June 26, 2008.
 B4-622, and B4-622R airplanes           Appendices 1, 2, and 3.
A310 series airplanes.................  A310-54-2018, excluding                 02  June 26, 2008.
                                         Appendices 1, 2, and 3.
----------------------------------------------------------------------------------------------------------------

     (9) Inspections and corrective actions accomplished prior to 
the effective date of this AD in accordance with the service 
bulletins identified in Table 3 of this AD, as applicable, are 
acceptable for compliance with the corresponding requirements of 
this AD.

                  Table 3--Previous Service Information
------------------------------------------------------------------------
     Service Bulletin--          Revision--             Dated--
------------------------------------------------------------------------
Airbus Mandatory Service      01.............  November 9, 2007.
 Bulletin A300-54-0075.
Airbus Mandatory Service      01.............  November 9, 2007.
 Bulletin A300-54-6015.
Airbus Mandatory Service      01.............  November 16, 2007.
 Bulletin A310-54-2018.
Airbus Service Bulletin A300- Original.......  August 11, 1993.
 54-0075.
Airbus Service Bulletin A300- Original.......  August 11, 1993.
 54-6015.
Airbus Service Bulletin A310- Original.......  August 11, 1993.
 54-2018.
------------------------------------------------------------------------

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows:
    (1) Although the MCAI/service information allows further flight 
after cracks are found during compliance with certain actions, this 
AD requires that you repair the crack(s) before further flight.
    (2) Although the MCAI specifies to send all inspection results 
to Airbus, this AD does not include that requirement.

Other FAA AD Provisions

    (g) 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, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. Before 
using any approved AMOC on any airplane to which the AMOC applies, 
notify your appropriate principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards 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.
    (3) Reporting Requirements: For any reporting requirement in 
this AD, under the provisions of the Paperwork Reduction Act (44 
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has 
approved the information collection requirements and has assigned 
OMB Control Number 2120-0056.

Related Information

    (h) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2008-0181, dated October 1, 2008, and the applicable 
service bulletins identified in Table 2 of this AD, for related 
information.

Material Incorporated by Reference

    (i) You must use the service information specified in Table 4 of 
this AD, as applicable, to do the actions required by this AD, 
unless the AD specifies otherwise.

                      Table 4--Service Information
------------------------------------------------------------------------
  Airbus Mandatory Service
         Bulletin--              Revision--             Dated--
------------------------------------------------------------------------
A300-54-0075, excluding       02.............  June 26, 2008.
 Appendices 1, 2, and 3.
A300-54-6015, excluding       02.............  June 26, 2008.
 Appendices 1, 2, and 3.
A310-54-2018, excluding       02.............  June 26, 2008.
 Appendices 1, 2, and 3.
------------------------------------------------------------------------

     (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) 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: account.airworth-eas@airbus.com; 
Internet http://www.airbus.com.
    (3) 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 or 425-227-1152.

[[Page 11433]]

    (4) 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 March 4, 2010.
Suzanne Masterson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-5162 Filed 3-10-10; 8:45 am]
BILLING CODE 4910-13-P
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