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[Federal Register Volume 76, Number 91 (Wednesday, May 11, 2011)]
[Rules and Regulations]
[Pages 27220-27227]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-10684]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1275; Directorate Identifier 2010-NM-091-AD; 
Amendment 39-16688; AD 2011-10-07]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A310 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This AD results from mandatory continuing 
airworthiness information (MCA I) 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:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France Airworthiness Directive (AD) 1992-106-132(B) * * * was issued 
to require a set of inspection- and modification tasks which 
addressed JAR/FAR [Joint Aviation Regulation/Federal Aviation 
Regulation] 25-571 requirements related to damage-tolerance and 
fatigue evaluation of structure.
* * * * *
The unsafe condition is reduced structural integrity of the wings. We 
are issuing this AD to require actions to correct the unsafe condition 
on these products.

DATES: This AD becomes effective June 15, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 15, 
2011.

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 January 3, 2011 (76 
FR 34). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France Airworthiness Directive (AD) 1992-106-132(B) original issue 
up to revision 7 was issued to require a set of inspection- and 
modification tasks which addressed JAR/FAR [Joint Aviation 
Regulation/Federal Aviation Regulation] 25-571 requirements related 
to damage-tolerance and fatigue evaluation of structure [FAA AD 98-
26-01 corresponds to DGAC AD 1992-106-132(B)R4, dated June 5, 1996].
    Following the Extended Design Service Goal activities as part of 
the Structure Task Group for the Airbus A310 program, EASA issued AD 
2007-0053 which replaced DGAC France AD F-1992-106-132R7. Since the 
issuance of that AD, the thresholds and the intervals of some Airbus 
Service Bulletins (SBs which address structure fatigue related areas 
on the wing parts), until now part of the requirements of AD 2007-
0053, have been updated.
    For the reasons stated above, this new [EASA] AD requires the 
accomplishment of the structural fatigue-related corrective actions 
in accordance with the latest revision of these SBs which have been 
reviewed in the context of the A310 Extended Service Goal 
activities. Consequently, this new AD supersedes the requirements of 
paragraphs 1.8, 1.9, 1.10, 1.13, 1.18 of EASA AD 2007-0053, which 
has been revised accordingly.

The unsafe condition is reduced structural integrity of the wings. The 
required corrective actions are as follows, depending on airplane 
configuration:
     For certain Model A310-203 and A310-222 airplanes: 
Repetitive detailed inspections for cracking of the leading edge access 
panels around the bolt holes, and repair if necessary.
     For certain Model A310-203, A310-204, A310-222, A310-304, 
A310-322, A310-324, and A310-325 airplanes: Repetitive eddy current 
inspections to detect cracks in the holes around the overwing refueling 
aperture at ribs 13-14, and repair if necessary.
     For certain Model A310-203, A310-204, A310-222, A310-304, 
A310-322, A310-324, and A310-325 airplanes: Repetitive external 
detailed inspections for cracking of the top skin at ribs 13-14, 
repetitive internal detailed inspections for cracking of stringer 7 and 
stringer 8 of the overwing refuel aperture, and repair if necessary.
     For certain Model A310-203 and A310-222 airplanes: 
Repetitive detailed inspections for cracking around the bolts in the 
wing top skin upper surface of the front spar between rib 7 and rib 28, 
and repair if necessary.
     For certain Model A310-203 and A310-222 airplanes: 
Repetitive high frequency eddy current (HFEC) or X-ray inspections to 
detect cracking of the stringer runouts inboard and outboard of rib 14 
at stringers 6, 7, 8, and 9, and repair if necessary.
     For certain Model A310-203, A310-204, A310-222, A310-304, 
A310-322, and A310-324 airplanes: Repetitive ultrasonic inspections for 
cracking in certain bolt holes where the main landing gear forward 
pick-up fitting is attached to the rear spar, and repair if necessary.
    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.

Explanation of Changes to This AD

    We have moved the parenthetical information from paragraphs (g), 
(i), (j), (o), and (q)(1), (q)(2), and (q)(3) of this AD. Instead, we 
have provided that information in Note 1, Note 3, Note 4, Note 6, and 
Note 8 of this AD.
    We have also revised tables 3 and 4 of this AD to refer to Model 
``A310-322'' instead of ``A310A-322.'' We inadvertently referred to 
``A310A-322'' in the NPRM.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD with the changes described 
previously. We determined that these change 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

[[Page 27221]]

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 44 products of U.S. registry. 
We also estimate that it will take about 97 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 $362,780, or $8,245 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.

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 adding the following new AD:

2011-10-07 Airbus: Amendment 39-16688. Docket No. FAA-2010-1275; 
Directorate Identifier 2010-NM-091-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 15, 
2011.

Affected ADs

    (b) This AD affects AD 90-19-07, Amendment 39-6731 (55 FR 37455, 
September 12, 1990); and AD 91-06-18, Amendment 39-6940 (56 FR 
10796, March 14, 1991).

Applicability

    (c) This AD applies to Airbus Model A310-203, -204, -221, -222, 
-304, -322, -324, and -325 airplanes, certificated in any category, 
all certified models, all serial numbers.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France Airworthiness Directive (AD) 1992-106-132(B) * * * was issued 
to require a set of inspection- and modification tasks which 
addressed JAR/FAR [Joint Aviation Regulation/Federal Aviation 
Regulation] 25-571 requirements related to damage-tolerance and 
fatigue evaluation of structure.
* * * * *
    The unsafe condition is reduced structural integrity of the 
wings.

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 98-26-01, Amendment 39-10942 
(63 FR 69179, December 16, 1998), With Reduced Compliance Times

Leading Edge Access Panels Landing--Lower Skin--Inspection for Cracks 
at Bolt Holes

    (g) For Model A310-203 and A310-222 airplanes listed in Airbus 
Service Bulletin A310-57-2002, Revision 2, dated January 4, 1996, 
except airplanes on which Airbus modification No. 05101 has been 
embodied in production, or on which Airbus Service Bulletin A310-57-
2003 has been embodied in service before the accumulation of 9,400 
total flight cycles and 18,800 total flight hours: At the times 
specified in paragraph (h) of this AD, perform a detailed visual 
inspection to detect cracks in the external surface of the wing 
lower skin around the landing access panel holes of the leading 
edge, in accordance with the Airbus Service Bulletin A310-57-2002, 
Revision 1, dated July 2, 1992; Airbus Service Bulletin A310-57-
2002, Revision 2, dated January 4, 1996; or Airbus Mandatory Service 
Bulletin A310-57-2002, Revision 03, dated November 28, 2006. If any 
discrepancy is found, prior to further flight, repair in accordance 
with a method approved by either the Manager, International Branch, 
ANM-116, FAA, Transport Airplane Directorate, or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated 
agent) or EASA (or its delegated agent). Except as required by 
paragraph (n) of this AD, repeat the detailed inspection specified 
in this paragraph at the earlier of the times specified in 
paragraphs (g)(1) and (g)(2) of this AD; and thereafter at intervals 
not to exceed 2,300 flight cycles or 4,700 flight hours, whichever 
occurs first. As of the effective date of this AD, use only Airbus 
Mandatory Service Bulletin A310-57-2002, Revision 03, dated November 
28, 2006. Accomplishment of Airbus Modification 05101 before the 
effective date of this AD terminates the repetitive inspection 
requirements of this paragraph; however, airplanes identified in 
paragraph (n) of this AD are applicable to the new inspections 
required by paragraph (n) of this AD. As of the effective date of 
this AD: Accomplishment of Airbus Modification 05101 before the 
accumulation of 9,400 total flight cycles and 18,800 total flight 
hours terminates the repetitive inspection requirements of this 
paragraph.

    Note 1: Airbus Service Bulletin A310-57-2003, Revision 03, dated 
October 16, 2006, is

[[Page 27222]]

an additional source of guidance for accomplishing Airbus 
Modification 05101.

    Note 2: As of the effective date of this AD, if Airbus Service 
Bulletin A310-57-2003 is done on or after the accumulation of 9,400 
total flight cycles or on or after the accumulation of 18,800 total 
flight hours, the actions specified in paragraph (g) of this AD are 
still required.

    (1) Within 3,000 flight cycles after doing the detailed 
inspection specified in paragraph (g) of this AD.
    (2) At the later of the times specified in paragraphs (g)(2)(i) 
and (g)(2)(ii) of this AD.
    (i) Within 2,300 flight cycles or 4,700 flight hours, whichever 
occurs first, after doing the detailed inspection required by 
paragraph (g) of this AD.
    (ii) Within 1,500 flight cycles or 3,000 flight hours, whichever 
occurs first, after the effective date of this AD.
    (h) For Model A310-203 and A310-222 airplanes listed in Airbus 
Service Bulletin A310-57-2002, Revision 2, dated January 4, 1996, 
except airplanes on which Airbus modification No. 05101 has been 
embodied in production, or on which Airbus Service Bulletin A310-57-
2003 has been embodied in service before the accumulation of 9,400 
total flight cycles and 18,800 total flight hours: At the earlier of 
the times specified in paragraphs (h)(1) and (h)(2) of this AD, do 
the detailed inspection required by paragraph (g) of this AD.
    (1) Prior to the accumulation of 12,000 total flight cycles, or 
within 1,000 flight cycles after January 20, 1999 (the effective 
date of AD 98-26-01, amendment 39-10942), whichever occurs later.
    (2) At the later of the times specified in paragraph (h)(2)(i) 
and (h)(2)(ii) of this AD.
    (i) Prior to the accumulation of 9,400 total flight cycles or 
18,800 total flight hours, whichever occurs first.
    (ii) Within 1,500 flight cycles or 3,000 flight hours, whichever 
occurs first, after the effective date of this AD.

Inspect Area around Overwing Refueling Aperture at Ribs 13-14

    (i) For Model A310-203, A310-204, A310-222, A310-304, A310-322, 
A310-324, and A310-325 airplanes that are listed in Airbus Service 
Bulletin A310-57-2006, Revision 3, dated May 2, 1996, and are 
identified as Configuration 1 in Airbus Mandatory Service Bulletin 
A310-57-2006, Revision 04, dated May 21, 2007: Prior to the 
accumulation of 6,000 total flight cycles, or within 1,000 flight 
cycles after January 20, 1999, whichever occurs later, perform an 
eddy current inspection to detect cracks in the holes around the 
overwing refueling aperture at ribs 13-14, in accordance with Airbus 
Service Bulletin A310-57-2006, Revision 3, dated May 2, 1996; or 
Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated 
May 21, 2007. If any discrepancy is found, prior to further flight, 
perform follow-on corrective actions, as applicable, in accordance 
with Airbus Service Bulletin A310-57-2006, Revision 3, dated May 2, 
1996; or Airbus Mandatory Service Bulletin A310-57-2006, Revision 
04, dated May 21, 2007; except where the service bulletin specifies 
to contact Airbus for repair, before further flight, repair in 
accordance with a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
or the DGAC (or its delegated agent) or EASA (or its delegated 
agent). Repeat the inspection specified in this paragraph at the 
earlier of the times specified in paragraphs (i)(1) and (i)(2) of 
this AD, and thereafter at intervals not to exceed 2,300 flight 
cycles or 4,600 flight hours, whichever occurs first. As of the 
effective date of this AD, use only Airbus Mandatory Service 
Bulletin A310-57-2006, Revision 04, dated May 21, 2007. 
Accomplishment of Airbus Modification 05891H5128 terminates the 
repetitive inspections required by this paragraph.
    (1) Within 3,000 flight cycles after doing the last inspection 
required by paragraph (i) of this AD.
    (2) At the later of the times specified in paragraphs (i)(2)(i) 
and (i)(2)(ii) of this AD.
    (i) Within 2,300 flight cycles or 4,600 flight hours, whichever 
occurs first, after doing the most recent inspection required by 
paragraph (i) of this AD.
    (ii) Within 380 flight cycles or 770 flight hours, whichever 
occurs first, after the effective date of this AD.

    Note 3:  Airbus Service Bulletin A310-57-2020, Revision 07, 
dated June 5, 2006, is an additional source of guidance for 
accomplishing Airbus Modification 05891H5128.

Upper Skin Forward of Front Spar--Inspection for Cracks

    (j) For Model A310-203 and A310-222 airplanes listed in Airbus 
Service Bulletin A310-57-2032, Revision 3, dated January 4, 1996, 
except airplanes on which Airbus modification 05026 has been 
embodied in production, or on which Airbus Service Bulletin A310-57-
2005 has been done in service before the accumulation of 10,500 
total flight cycles and 21,000 total flight hours: At the times 
specified in paragraph (k) of this AD, perform a detailed visual 
inspection to detect cracks around the bolts in the wing top skin 
upper surface of the front spar between rib 7 and rib 28, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A310-57-2032, Revision 3, dated January 4, 1996; or Airbus 
Mandatory Service Bulletin A310-57-2032, Revision 04, dated December 
1, 2006. If any discrepancy is found, prior to further flight, 
repair in accordance with a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
or DGAC (or its delegated agent) or EASA (or its delegated agent). 
Except as required by paragraph (p) of this AD, repeat the detailed 
inspection specified in this paragraph at the earlier of the times 
specified in paragraphs (j)(1) and (j)(2) of this AD, and thereafter 
at intervals not to exceed 3,900 flight cycles or 7,900 flight 
hours, whichever occurs first. As of the effective date of this AD, 
use only Airbus Mandatory Service Bulletin A310-57-2032, Revision 
04, dated December 1, 2006. Accomplishment of Airbus Modification 
05026H0878 before the effective date of this AD terminates the 
repetitive inspection requirements of this paragraph; however, 
airplanes identified in paragraph (p) of this AD are applicable to 
the new inspections required by paragraph (p) of this AD. As of the 
effective date of this AD: Accomplishment of Airbus Modification 
05026H0878 before the accumulation of 10,500 total flight cycles and 
21,000 total flight hours terminates the repetitive inspection 
requirements of this paragraph.
    (1) Within 4,500 flight cycles after doing the last inspection 
required by paragraph (j) of this AD.
    (2) At the later of the times specified in paragraphs (j)(2)(i) 
and (j)(2)(ii) of this AD.
    (i) Within 3,900 flight cycles or 7,900 flight hours, whichever 
occurs first, after doing the most recent inspection required by 
paragraph (j) of this AD.
    (ii) Within 850 flight cycles or 1,700 flight hours, whichever 
occurs first, after the effective date of this AD.

    Note 4: Airbus Service Bulletin A310-57-2005, Revision 03, dated 
October 2, 2006, is an additional source of guidance for 
accomplishing Airbus Modification 05026H0878.

    Note 5:  As of the effective date of this AD, if Airbus Service 
Bulletin A310-57-2005 is done on or after the accumulation of 10,500 
total flight cycles or on or after the accumulation of 21,000 total 
flight hours, the actions specified in paragraph (j) of this AD are 
still required.

    (k) For Model A310-203 and A310-222 airplanes listed in Airbus 
Service Bulletin A310-57-2032, Revision 3, dated January 4, 1996, 
except airplanes on which Airbus modification 05026 has been 
embodied in production, or on which Airbus Service Bulletin A310-57-
2005 has been done in service before the accumulation of 10,500 
total flight cycles and 21,000 total flight hours: At the earlier of 
the times specified in paragraphs (k)(1) and (k)(2) of this AD, do 
the detailed inspection required by paragraph (j) of this AD.
    (1) Prior to the accumulation of 12,000 total flight cycles, or 
within 1,000 flight cycles after January 20, 1999, whichever occurs 
later.
    (2) At the later of the times specified in paragraphs (k)(2)(i) 
and (k)(2)(ii) of this AD.
    (i) Prior to the accumulation of 10,500 total flight cycles or 
21,000 total flight hours, whichever occurs first.
    (ii) Within 850 flight cycles or 1,700 flight hours, whichever 
occurs first, after the effective date of this AD.

Stringer Flanges at Rib 14 Wing Bottom Skin--Inspect for Cracks

    (l) For Model A310-203 and A310-222 airplanes listed in Airbus 
Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996, 
except airplanes on which Airbus modification 04987 has been done in 
production: At the compliance time specified in paragraph (m) of 
this AD, perform a high frequency eddy current (HFEC) or X-ray 
inspection to detect cracking of the stringer runouts inboard and 
outboard of rib 14 at stringers 6, 7, 8, and 9, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A310-57-
2038, Revision 2, dated January 4, 1996; or Airbus Mandatory

[[Page 27223]]

Service Bulletin A310-57-2038, Revision 04, dated October 19, 2006. 
Do the next inspection at the earlier of the times specified in 
paragraph (l)(1) and (l)(2) of this AD, and repeat the inspection 
thereafter at intervals not to exceed the applicable times specified 
in table 1 of this AD. If any crack is detected, prior to further 
flight, repair in accordance with a method approved by either the 
Manager, International Branch, ANM-116, FAA, Transport Airplane 
Directorate, or DGAC (or its delegated agent) or EASA (or its 
delegated agent). As of the effective date of this AD, use only 
Airbus Mandatory Service Bulletin A310-57-2038, Revision 04, dated 
October 19, 2006.
    (1) Within the applicable interval specified in paragraph 
1.B.(5) of Airbus Service Bulletin A310-57-2038, Revision 2, dated 
January 4, 1996.
    (2) At the later of the times specified in paragraph (l)(2)(i) 
and (l)(2)(ii) of this AD.
    (i) Within the applicable interval specified in table 1 of this 
AD after doing the most recent inspection specified in paragraph (l) 
of this AD.
    (ii) Within 1,100 flight cycles or 2,300 flight hours, whichever 
occurs first, after the effective date of this AD.

       Table 1--Repetitive Intervals, Depending on Inspection Type
------------------------------------------------------------------------
                                           Repetitive interval (not to
          Type of  inspection                        exceed)
------------------------------------------------------------------------
X-Ray..................................  7,200 flight cycles or 14,500
                                          flight hours, whichever occurs
                                          first.
HFEC...................................  9,400 flight cycles or 18,800
                                          flight hours, whichever occurs
                                          first.
------------------------------------------------------------------------

    (m) For Model A310-203 and A310-222 airplanes listed in Airbus 
Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996, 
except airplanes on which Airbus modification 04987 has been done in 
production: At the earlier of the times specified in paragraphs 
(m)(1) and (m)(2) of this AD, perform an inspection required by 
paragraph (l) of this AD.
    (1) Prior to the accumulation of 12,000 total flight cycles, or 
within 1,500 flight cycles after January 20, 1999, whichever occurs 
later.
    (2) At the later of the times specified in paragraphs (m)(2)(i) 
and (m)(2)(ii) of this AD.
    (i) Prior to the accumulation of 12,000 total flight cycles or 
24,000 total flight hours, whichever occurs first.
    (ii) Within 1,100 flight cycles or 2,300 flight hours after the 
effective date of this AD, whichever occurs first.

New Requirements of This AD

Leading Edge Access Panels Landing--Lower Skin--Inspection for Cracks 
at Bolt Holes--Additional Inspections for Certain Airplanes

    (n) For Model A310-203 and A310-222 airplanes, on which Airbus 
Service Bulletin A310-57-2003 has been done in service on or after 
the accumulation of 9,400 total flight cycles or on or after the 
accumulation of 18,800 total flight hours: Do the inspection 
required by paragraph (g) of this AD at the later of the times 
specified in paragraphs (n)(1) and (n)(2) of this AD. Repeat the 
inspection required by paragraph (g) of this AD thereafter at 
intervals not to exceed 2,300 flight cycles or 4,700 flight hours, 
whichever occurs first.
    (1) Within 2,300 flight cycles or 4,700 flight hours, whichever 
occurs first, after doing the most recent detailed inspection 
required by paragraph (g) of this AD.
    (2) Within 1,500 flight cycles or 3,000 flight hours, after the 
effective date of this AD, whichever occurs first.

Inspect Area Around Overwing Refueling Aperture at Ribs 13-14 for 
Additional Airplanes

    (o) For Model A310-203, A310-204, A310-222, A310-304, A310-322, 
A310-324, and A310-325 airplanes, except for airplanes identified in 
paragraph (i) of this AD on which Airbus Modification 05891H5128 has 
not been done: At the applicable compliance time specified in table 
2 of this AD, do the applicable actions specified in paragraph 
(o)(1) or (o)(2) of this AD, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A310-57-2006, 
Revision 04, dated May 21, 2007. If any cracking is found, before 
further flight, repair in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A310-57-2006, 
Revision 04, dated May 21, 2007; except where this service bulletin 
specifies to contact Airbus for repair, before further flight, 
repair in accordance with a method approved by either the Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
or EASA (or its delegated agent). Repeat the inspections thereafter 
at the applicable interval specified in table 2 of this AD. Certain 
compliance times specified in table 2 of this AD are applicable to 
short range use, average flight time (AFT) equal to or less than 4.0 
hours, or long range use, AFT exceeding 4.0 hours. For airplanes 
identified as Configuration 01 in Airbus Mandatory Service Bulletin 
A310-57-2006, Revision 04, dated May 21, 2007, accomplishment of 
Airbus Modification 05891H5128 terminates the repetitive inspections 
required by this paragraph for Configuration 01 airplanes; 
thereafter do the applicable actions specified in paragraph (o)(2) 
of this AD at the times specified in table 2 of this AD.

    Note 6: Airbus Service Bulletin A310-57-2020, Revision 07, dated 
June 5, 2006, is an additional source of guidance for accomplishing 
Airbus Modification 05891H5128.

    (1) For Configuration 01 airplanes, as identified in Airbus 
Mandatory Service Bulletin A310-57-2006, Revision 04, dated May 21, 
2007: Do a rotating probe eddy current inspection for cracking in 
the holes around the overwing refueling aperture at ribs 13-14.
    (2) For Configuration 02 through 06 airplanes, as identified in 
Airbus Mandatory Service Bulletin A310-57-2006, Revision 04, dated 
May 21, 2007: Do an external detailed inspection for cracking of the 
top skin at ribs 13-14, and an internal detailed inspection for 
cracking of string 7 and string 8 of the overwing refuel aperture.

                       Table 2--Compliance Times for Configuration 01 Through 06 Airplanes
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
  Airplanes as Identified in Airbus        Compliance time (whichever occurs later)        Repetitive interval
 Mandatory Service Bulletin A310-57-                                                          (not to exceed)
2006, revision 04, dated May 21, 2007
----------------------------------------------------------------------------------------------------------------
Configuration 01 airplanes...........  Prior to the             Within 380 flight        2,300 flight cycles or
                                        accumulation of 6,000    cycles or 770 flight     4,600 flight hours,
                                        total flight cycles.     hours, whichever         whichever occurs
                                                                 occurs first, after      first.
                                                                 the effective date of
                                                                 this AD.
Configuration 02 airplanes...........  Within 30,900 flight     Within 1,500 flight      11,300 flight cycles or
                                        cycles or 61,900         cycles or 18 months,     22,600 flight hours,
                                        flight hours,            whichever occurs         whichever occurs
                                        whichever occurs         first, after the         first.
                                        first, after             effective date of this
                                        accomplishing Airbus     AD.
                                        Service Bulletin A310-
                                        57-2020.
Configuration 03 airplanes...........  Within 30,900 flight     Within 1,500 flight      12,000 flight cycles or
                                        cycles or 61,900         cycles or 18 months,     24,000 flight hours,
                                        flight hours,            whichever occurs         whichever occurs
                                        whichever occurs         first, after the         first.
                                        first, after Airbus      effective date of this
                                        Modification             AD.
                                        05891H5128 is done or
                                        Airbus Service
                                        Bulletin A310-57-2020
                                        is accomplished.

[[Page 27224]]

 
Configuration 04 and 05 short range    Before the accumulation  Within 1,500 flight      12,000 flight cycles or
 airplanes.                             of 25,900 total flight   cycles or 18 months,     33,600 flight hours,
                                        cycles or 72,500 total   whichever occurs         whichever occurs
                                        flight hours,            first, after the         first.
                                        whichever occurs first.  effective date of this
                                                                 AD.
Configuration 04 and 05 long range     Before the accumulation  Within 1,500 flight      9,400 flight cycles or
 airplanes.                             of 18,800 total flight   cycles or 18 months,     47,200 flight hours,
                                        cycles or 94,200 total   whichever occurs         whichever occurs
                                        flight hours,            first, after the         first.
                                        whichever occurs first.  effective date of this
                                                                 AD.
Configuration 06.....................  Before the accumulation  Within 1,500 flight      12,000 flight cycles or
                                        of 30,900 total flight   cycles or 18 months,     24,000 flight hours,
                                        cycles or 61,900 total   whichever occurs         whichever occurs
                                        flight hours,            first, after the         first.
                                        whichever occurs first.  effective date of this
                                                                 AD.
----------------------------------------------------------------------------------------------------------------

Upper Skin Forward of Front Spar--Inspection for Cracks--Additional 
Inspections for Certain Airplanes

    (p) For Model A310-203 and A310-222 airplanes on which Airbus 
Service Bulletin A310-57-2005 has been done in service on or after 
the accumulation of 10,500 total flight cycles or on or after 21,000 
total flight hours: Do the inspection required by paragraph (j) of 
this AD at the later of the times specified in paragraphs (p)(1) and 
(p)(2) of this AD. Repeat the inspection specified in paragraph (j) 
of this AD thereafter at intervals not to exceed 3,900 flight cycles 
or 7,900 flight hours, whichever occurs first.
    (1) Within 3,900 flight cycles or 7,900 flight hours, whichever 
occurs first, after doing the most recent inspection required by 
paragraph (j) of this AD.
    (2) Within 850 flight cycles or 1,700 flight hours, whichever 
occurs first, after the effective date of this AD.

Inspection of Rear Spar at Selected Bolt Locations for Attachment of 
Main landing Gear Forward Pick-Up Fitting

    (q) For Model A310-203, A310-204, A310-222, A310-304, A310-322, 
and A310-324 airplanes, except airplanes on which Airbus 
modification 07601 has been done in production: Do the applicable 
actions specified in paragraphs (q)(1), (q)(2), and (q)(3) of this 
AD. If any cracking is found during any inspection, before further 
flight, repair in accordance with a method approved by either the 
Manager, International Branch, ANM-116, FAA, Transport Airplane 
Directorate, or EASA (or its delegated agent).

    Note 7:  For Model A310-304, A310-322, and A310-324 airplanes on 
which Airbus modification 07601 has been done, guidance for post-
modification inspections can be found in Structure Significant Item 
(SSI) 57.21.16 of the Maintenance Review Board Document (MRBD).

    (1) For airplanes on which Airbus Modification 07925H1113 and 
Modification 11578H5436 have not been done: At the applicable time 
specified in table 3 of this AD, perform an ultrasonic inspection 
for cracking in certain bolt holes where the main landing gear 
forward pick-up fitting is attached to the rear spar, in accordance 
with the Accomplishment Instructions of Airbus Mandatory Service 
Bulletin A310-57-2046, Revision 08, dated December 1, 2006. Repeat 
the inspection thereafter at the applicable interval specified in 
table 3 of this AD until Airbus Modification 07925H1113 or 
11578H5436 has been done. After doing Airbus Modification 07925H1113 
or 11578H5436 do the applicable actions specified in paragraph 
(q)(2) or (q)(3) of this AD at the times specified in paragraph 
(q)(2) or (q)(3) of this AD, as applicable. Certain compliance times 
specified in table 3 of this AD are applicable to short range use, 
average flight time (AFT) equal to or less than 4.0 hours, or long 
range use, AFT exceeding 4.0 hours.

    Note 8: Airbus Service Bulletin A310-57-2049, Revision 6, dated 
November 26, 1997, is an additional source of guidance for 
accomplishing Airbus Modification 07925H1113. Airbus Service 
Bulletin A310-57-2074, Revision 03, dated July 3, 2006, is an 
additional source of guidance for accomplishing Airbus Modification 
11578H5436.

                     Table 3--Compliance Times for Airplanes Pre-Mod 07925 and Pre-Mod 11578
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
              Airplanes                    Compliance time (whichever occurs later)        Repetitive interval
                                                                                              (not to exceed)
----------------------------------------------------------------------------------------------------------------
Model A310-203, A310-204, and A310-    Prior to the             Within 750 flight        2,800 flight cycles or
 222 airplanes.                         accumulation of 9,800    cycles or 1,500 flight   5,700 flight hours,
                                        total flight cycles or   hours, whichever         whichever occurs
                                        19,600 total flight      occurs first, after      first.
                                        hours, whichever         the effective date of
                                        occurs first.            this AD.
Model A310-304, A310-322, and A310-    Prior to the             Within 750 flight        2,400 flight cycles or
 324 short range airplanes.             accumulation of 7,100    cycles or 1,500 flight   6,900 flight hours,
                                        total flight cycles or   hours, whichever         whichever occurs
                                        20,100 total flight      occurs first, after      first.
                                        hours, whichever         the effective date of
                                        occurs first.            this AD.
Model A310-304, A310-322, and A310-    Prior to the             Within 750 flight        1,900 flight cycles or
 324 long range airplanes.              accumulation of 5,700    cycles or 1,500 flight   9,800 flight hours,
                                        total flight cycles or   hours, whichever         whichever occurs
                                        28,600 total flight      occurs first, after      first.
                                        hours, whichever         the effective date of
                                        occurs first.            this AD.
----------------------------------------------------------------------------------------------------------------

    (2) For airplanes on which Airbus Modification 07925H1113 has 
been done: At the applicable time specified in table 4 of this AD, 
perform an ultrasonic inspection for cracking in certain bolt holes 
where the main landing gear forward pick-up fitting is attached to 
the rear spar, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated 
December 1, 2006. Repeat the inspection thereafter at the applicable 
interval specified in table 4 of this AD. Certain compliance times 
specified in table 4 of this AD are applicable to short range use, 
AFT equal to or less than 4.0 hours, or long range use, AFT 
exceeding 4.0 hours.

[[Page 27225]]

                             Table 4--Compliance Times for Airplanes Post-Mod 07925
----------------------------------------------------------------------------------------------------------------
                  --                              --                       --                       --
----------------------------------------------------------------------------------------------------------------
              Airplanes                    Compliance time (whichever occurs later)        Repetitive interval
                                                                                              (not to exceed)
----------------------------------------------------------------------------------------------------------------
Model A310-203, A310-204, and A310-    Prior to the             Within 750 flight        9,400 flight cycles or
 222 airplanes.                         accumulation of 14,700   cycles or 1,500 flight   18,900 flight hours,
                                        total flight cycles or   hours, whichever         whichever occurs
                                        29,400 total flight      occurs first, after      first.
                                        hours, whichever         the effective date of
                                        occurs first.            this AD.
Model A310-304, A310-322, and A310-    Prior to the             Within 750 flight        5,000 flight cycles or
 324 short range airplanes.             accumulation of 11,900   cycles or 1,500 flight   14,000 flight hours,
                                        total flight cycles or   hours, whichever         whichever occurs
                                        33,500 total flight      occurs first, after      first.
                                        hours, whichever         the effective date of
                                        occurs first.            this AD.
Model A310-304, A310-322, and A310-    Prior to the             Within 750 flight        4,000 flight cycles or
 324 long range airplanes.              accumulation of 9,500    cycles or 1,500 flight   20,000 flight hours,
                                        total flight cycles or   hours, whichever         whichever occurs
                                        47,700 total flight      occurs first, after      first.
                                        hours, whichever         the effective date of
                                        occurs first.            this AD.
----------------------------------------------------------------------------------------------------------------

     (3) For airplanes on which Airbus Modification 11578H5436 has 
been done: At the applicable time specified in table 5 of this AD, 
perform an ultrasonic inspection for cracking in certain bolt holes 
where the main landing gear forward pick-up fitting is attached to 
the rear spar, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A310-57-2046, Revision 08, dated 
December 1, 2006. Repeat the inspection thereafter at the applicable 
interval specified in table 5 of this AD. Certain compliance times 
specified in table 5 of this AD are applicable to short range use, 
average flight time (AFT) equal to or less than 4.0 hours, or long 
range use, AFT exceeding 4.0 hours.

                             Table 5--Compliance Times for Airplanes Post-Mod 11578
----------------------------------------------------------------------------------------------------------------
 
----------------------------------------------------------------------------------------------------------------
              Airplanes                    Compliance time (whichever occurs later)        Repetitive interval
                                                                                              (not to exceed)
----------------------------------------------------------------------------------------------------------------
Model A310-203, A310-204, and A310-    Within 29,600 flight     Within 750 flight        9,400 flight cycles or
 222 airplanes.                         cycles or 59,200         cycles or 1,500 flight   18,900 flight hours,
                                        flight hours,            hours, whichever         whichever occurs
                                        whichever occurs         occurs first, after      first.
                                        first, after Airbus      the effective date of
                                        Modification             this AD.
                                        11578H5436 has been
                                        done.
Model A310-304, A310-322, and A310-    Within 24,200 flight     Within 750 flight        5,000 flight cycles or
 324 short range airplanes.             cycles or 67,900         cycles or 1,500 flight   14,000 flight hours,
                                        flight hours,            hours, whichever         whichever occurs
                                        whichever occurs         occurs first, after      first.
                                        first, after Airbus      the effective date of
                                        Modification             this AD.
                                        11578H5436 has been
                                        done.
Model A310-304, A310-322, and A310-    Within 19,300 flight     Within 750 flight        4,000 flight cycles or
 324 long range airplanes.              cycles or 96,800         cycles or 1,500 flight   20,000 flight hours,
                                        flight hours,            hours, whichever         whichever occurs
                                        whichever occurs         occurs first, after      first.
                                        first, after Airbus      the effective date of
                                        Modification             this AD.
                                        11578H5436 has been
                                        done.
----------------------------------------------------------------------------------------------------------------

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (r) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin A310-57-2038, Revision 03, 
dated September 4, 1998, are acceptable for compliance with the 
corresponding actions specified in paragraph (l) of this AD.
    (s) Actions done before the effective date of this AD in 
accordance with Airbus Service Bulletin A310-57-2046, Revision 07, 
dated April 2, 1999, are acceptable for compliance with the 
corresponding actions specified in paragraph (q) of this AD.

Terminating Action for Paragraph (a) of AD 90-19-07

    (t) Accomplishing an inspection in accordance with Airbus 
Service Bulletin A310-57-2038, Revision 2, dated January 4, 1996, or 
Revision 03, dated September 4, 1998; or Airbus Mandatory Service 
Bulletin A310-57-2038, Revision 04, dated October 19, 2006; 
terminates the requirements of paragraph (a) of AD 90-19-07.

    Note 9: Airbus Service Bulletin A310-57-2038, Revision 2, dated 
January 4, 1996; and Airbus Mandatory Service Bulletin A310-57-2038, 
Revision 04, dated October 19, 2006; are referred to in paragraph 
(l) of this AD. Airbus Service Bulletin A310-57-2038, Revision 03, 
dated September 4, 1998, is referred to in paragraph (r) of this AD.

Terminating Action for AD 91-06-18

    (u) Accomplishing an inspection in accordance with Airbus 
Service Bulletin A310-57-2046, Revision 4, dated October 16, 1996, 
as revised by Airbus Service Bulletin Change Notice 4A, dated 
October 16, 1996; Airbus Service Bulletin A310-57-2046, Revision 07, 
dated April 2, 1999; or Airbus Mandatory Service Bulletin A310-57-
2046, Revision 08, dated December 1, 2006; terminates the 
requirements of AD 91-06-18.

    Note 10: Airbus Mandatory Service Bulletin A310-57-2046, 
Revision 08, dated December 1, 2006, is referred to in paragraph (q) 
of this AD. Airbus Service Bulletin A310-57-2046, Revision 07, dated 
April 2, 1999, is referred to in paragraph (s) of this AD. Airbus 
Service Bulletin A310-57-2046, Revision 4, dated October 16, 1996, 
as revised by Airbus Service Bulletin Change Notice 4A, dated 
October 16, 1996, is referred to in paragraph (n) of AD 98-26-01.

FAA AD Differences

    Note 11: This AD differs from the MCAI and/or service 
information as follows:
    Although the MCAI or service information allows further flight 
after cracks are found during compliance with the required action, 
paragraph (j) of this AD requires that you repair the crack(s) 
before further flight.

Other FAA AD Provisions

    (v) 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, Transport

[[Page 27226]]

Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. 
Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC, notify your 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 98-26-01, 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.

Related Information

    (w) Refer to MCAI EASA Airworthiness Directive 2007-0242, dated 
September 4, 2007, and the Airbus service bulletins listed in table 
6 of this AD for related information.

                                      Table 6--Related Service Information
----------------------------------------------------------------------------------------------------------------
            Service Bulletin                        Revision                              Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A310-   03..........................  November 28, 2006.
 57-2002.
Airbus Mandatory Service Bulletin A310-   04..........................  May 21, 2007.
 57-2006.
Airbus Mandatory Service Bulletin A310-   04..........................  December 1, 2006.
 57-2032.
Airbus Mandatory Service Bulletin A310-   04..........................  October 19, 2006.
 57-2038.
Airbus Mandatory Service Bulletin A310-   08..........................  December 1, 2006.
 57-2046.
Airbus Service Bulletin A310-57-2038....  2...........................  January 4, 1996.
Airbus Service Bulletin A310-57-2038....  03..........................  September 4, 1998
Airbus Service Bulletin A310-57-2046....  4...........................  October 16, 1996.
Airbus Service Bulletin A310-57-2046....  07..........................  April 2, 1999.
Airbus Service Bulletin A310-57-2046,     Original....................  October 16, 1996.
 Change Notice 4A.
----------------------------------------------------------------------------------------------------------------

Material Incorporated by Reference

    (x) You must use the service bulletins contained in table 7 of 
this AD to do the actions required by this AD, unless the AD 
specifies otherwise. If you accomplish the optional terminating 
actions specified by this AD, you must use the service information 
contained in table 7 of this AD to perform those actions unless the 
AD specifies otherwise.

                                 Table 7--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                                                                                            Required/optional
          Service Bulletin                    Revision                    Date                    action
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin     03......................  November 28, 2006......  Required.
 A310-57-2002.
Airbus Mandatory Service Bulletin     04......................  May 21, 2007...........  Required.
 A310-57-2006.
Airbus Mandatory Service Bulletin     04......................  December 1, 2006.......  Required.
 A310-57-2032.
Airbus Mandatory Service Bulletin     04......................  October 19, 2006.......  Required and optional.
 A310-57-2038.
Airbus Mandatory Service Bulletin     08......................  December 1, 2006.......  Required and optional.
 A310-57-2046.
Airbus Service Bulletin A310-57-2038  2.......................  January 4, 1996........  Optional.
Airbus Service Bulletin A310-57-2038  03......................  September 4, 1998......  Optional.
Airbus Service Bulletin A310-57-2046  4.......................  October 16, 1996.......  Optional.
Airbus Service Bulletin A310-57-2046  07......................  April 2, 1999..........  Optional.
Airbus Service Bulletin A310-57-      Original................  October 16, 1996.......  Optional.
 2046, Change Notice 4A.
----------------------------------------------------------------------------------------------------------------

     (1) The Director of the Federal Register approved the 
incorporation by reference of the service information contained in 
table 8 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.

                                 Table 8--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
                Service Bulletin                    Revision                           Date
----------------------------------------------------------------------------------------------------------------
Airbus Mandatory Service Bulletin A310-57-2002.              03  November 28, 2006.
Airbus Mandatory Service Bulletin A310-57-2006.              04  May 21, 2007.
Airbus Mandatory Service Bulletin A310-57-2032.              04  December 1, 2006.
Airbus Mandatory Service Bulletin A310-57-2038.              04  October 19, 2006.
Airbus Mandatory Service Bulletin A310-57-2046.              08  December 1, 2006.
Airbus Service Bulletin A310-57-2038...........              03  September 4, 1998.
Airbus Service Bulletin A310-57-2046...........              07  April 2, 1999.
----------------------------------------------------------------------------------------------------------------

     (2) The Director of the Federal Register previously approved 
the incorporation by reference of the service information contained 
in table 9 of this AD on January 20, 1999 (63 FR 69179, December 16, 
1998).

[[Page 27227]]

                             Table 9--Material Previously Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
            Service Bulletin                        Revision                              Date
----------------------------------------------------------------------------------------------------------------
Airbus Service Bulletin A310-57-2038....  2...........................  January 4, 1996.
Airbus Service Bulletin A310-57-2046....  4...........................  October 16, 1996.
Airbus Service Bulletin A310-57-2046,     Original....................  October 16, 1996.
 Change Notice 4A.
----------------------------------------------------------------------------------------------------------------

     (3) 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.
    (4) 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.
    (5) 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 April 22, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-10684 Filed 5-10-11; 8:45 am]
BILLING CODE 4910-13-P
```