[Federal Register Volume 76, Number 1 (Monday, January 3, 2011)]
[Proposed Rules]
[Pages 42-46]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-32983]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1276; Directorate Identifier 2010-NM-092-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede two existing ADs. This 
proposed AD results from mandatory continuing airworthiness information 
(MCAI) originated by an aviation authority of another country to 
identify and correct an unsafe condition on an aviation product. The 
MCAI describes the unsafe condition as:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France AD 1992-106-132(B) * * * has been issued in order to mandate 
a set of inspections/modifications which address 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, 
fuselage, and stabilizers. The proposed AD would require actions that 
are intended to address the unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by February 17, 
2011.

ADDRESSES: You may send comments by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: (202) 493-2251.
    <bullet> Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue, SE., Washington, DC 20590.
    <bullet> Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus SAS-EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; e-mail <a href="/cdn-cgi/l/email-protection#056466666a706b712b646c77726a77716d2860647645646c776770762b666a68"><span class="__cf_email__" data-cfemail="b3d2d0d0dcc6ddc79dd2dac1c4dcc1c7db9ed6d2c0f3d2dac1d1c6c09dd0dcde">[email protected]</span></a>; Internet http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2010-1276; 
Directorate Identifier 2010-NM-092-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this proposed AD.

Discussion

    On December 8, 1998, we issued AD 98-26-01, Amendment 39-10942 (63 
FR 69179, December 16, 1998); and on May 30, 1991, we issued AD 91-13-
01, Amendment 39-7032 (56 FR 26602, June 10, 1991). Those ADs required 
actions intended to address an unsafe condition on the products listed 
above.
    Since we issued ADs 98-26-01 and 91-13-01, we have determined that 
certain compliance times need to be reduced in order to adequately 
address the identified unsafe condition. The European Aviation Safety 
Agency (EASA), which is the Technical Agent for the Member States of 
the European Community, has issued EASA Airworthiness Directive 2007-
0053R3, dated December 17, 2009 (referred to after this as ``the 
MCAI''), to correct an unsafe condition for the specified products. The 
MCAI states:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France AD 1992-106-132(B) original issue up to revision 7 has been 
issued in order to mandate a set of inspections/modifications which 
address 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 part of 
the Structure Task Group for the A310 program, EASA AD 2007-0053 
superseded DGAC France AD F-1992-106-132R7 in order to take into 
account the publication of Airbus Service Bulletins (SB) A310-55-
2004 at Revision 5 and Airbus SB A310-53-2074 at Revision 3, whose 
inspection thresholds and/or intervals had been reduced.
    Revision 1 of this AD was issued to remove the mandatory 
requirements related to the wings (i.e. Sec.  1.8, 1.9, 1.10, 1.13, 
and 1.18) from the Compliance section, which have been transferred 
to EASA AD 2007-0242.
    Revision 2 of this AD has been issued to remove the mandatory 
requirements of paragraph 1.15, 1.16 and 1.17 which have now been 
transferred to EASA AD 2009-0057 (Sec.  1.15 and 1.17) and 2009-0058 
(Sec.  1.16) respectively.
    Revision 3 of this AD is issued to add a Note to the 
Applicability and amend the Required Action(s) and Compliance 
Time(s) section of this AD to clarify the allowed use of the 
referenced SBs by operators. In addition, a note has been added to 
paragraph 1.7 and the notes associated to paragraphs 1.1, 1.2, 1.3, 
1.4, 1.5 and 1.12 have been clarified.

The unsafe condition is reduced structural integrity of the wings, 
fuselage, and stabilizers. This NPRM proposes to continue to require 
certain actions specified in AD 98-26-01. This proposed AD also expands 
the inspection area of the high frequency eddy current rototest 
inspection

[[Page 43]]

required by paragraph (g) of AD 98-26-01. The required actions are as 
follows, depending on airplane configuration:
    <bullet> A defectoscope or rototest inspection to detect cracks in 
the area of frame 47 and frame 54, install new doublers, and repair if 
necessary.
    <bullet> Repetitive visual inspections to detect cracks on frame 46 
between the left- and right-hand sides of stringers 21 and 22 on the 
forward and aft faces, and repair if necessary.
    <bullet> Repetitive visual inspections to detect cracks at the T-
section connecting frame 50A to the beam between the left- and right-
hand sides of frames 50 and 51, and modification if necessary.
    <bullet> Repetitive visual inspections to detect cracks in the 
lower milled side panel at the lap joint with the upper side panel at 
frame 47 and stringer 22, left- and right-hand sides, and repair if 
necessary.
    <bullet> An eddy current inspection to detect cracks on the upper 
integral part adjacent to the rear attach fittings on the horizontal 
stabilizer, modification of the horizontal stabilizer, and repair if 
necessary.
    <bullet> Repetitive high frequency eddy current rototest 
inspections for cracking of the doubler plate edge, rear spar area, and 
at specified fastener holes in the top skin chordwise splice along the 
contour of the steel doubler between ribs 3 and 4 on the left- and 
right-hand center and side boxes on the horizontal stabilizer, 
installing new fasteners if no cracking is found, and repair if 
necessary.
    <bullet> Repetitive inspections, either an eddy current or visual 
inspection, to detect cracks on the left and right vertical posts, 
numbers 1 through 5 inclusive, in the wing center box at frame 40/41, 
and modification if necessary.
    You may obtain further information by examining the MCAI in the AD 
docket.

Other Relevant Rulemaking

    Certain paragraphs specified in AD 98-26-01 are not restated and 
are addressed by the following ADs and NPRMs.
    <bullet> AD 2009-01-09, Amendment 39-15788 (74 FR 8728, February 
26, 2009), addresses the actions specified in paragraph (a) of AD 98-
26-01.
    <bullet> AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 
2004), addresses the actions specified in paragraph (k) of AD 98-26-01.
    <bullet> AD 2006-09-05, Amendment 39-14575 (71 FR 25921, May 3, 
2006), addresses the actions specified in paragraph (o) of AD 98-26-01.
    <bullet> NPRM, Directorate Identifier 2010-NM-091-AD, addresses the 
actions specified in paragraphs (h), (i), (j), (m), (n), and (s) of AD 
98-26-01.
    <bullet> NPRM, Directorate Identifier 2010-NM-090-AD, addresses the 
action specified in paragraphs (p) and (r) of AD 98-26-01.
    <bullet> NPRM, Directorate Identifier 2010-NM-089-AD, addresses the 
action specified in paragraph (q) of AD 98-26-01.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A310-55-2004, Revision 
05, including Appendix 01, dated October 13, 2006; and Airbus Service 
Bulletin A310-53-2019, Revision 3, dated February 28, 1991. The actions 
described in this service information are intended to correct the 
unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

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

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a Note within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 44 products of U.S. registry.
    The actions that are required by AD 98-26-01 and retained in this 
proposed AD take about 1,087 work-hours per product, at an average 
labor rate of $85 per work hour. Required parts cost about $81,973 per 
product. Based on these figures, the estimated cost of the currently 
required actions is $174,368 per product.
    We estimate that it would take about 3 work-hours per product to 
comply with the new basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of the proposed AD on U.S. operators to be $11,220, or $255 
per product.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 44]]

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-10942 (63 FR 
69179, December 16, 1998) and Amendment 39-7032 (56 FR 26602, June 10, 
1991) and adding the following new AD:

Airbus: Docket No. FAA-2010-1276; Directorate Identifier 2010-NM-
092-AD.

Comments Due Date

    (a) We must receive comments by February 17, 2011.

Affected ADs

    (b) This AD supersedes AD 98-26-01, Amendment 39-10942, and AD 
91-13-01, Amendment 39-7032.

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 Codes 53: 
Fuselage, 55: Stabilizers, and 57: Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France AD 1992-106-132(B) original issue up to revision 7 has been 
issued in order to mandate a set of inspections/modifications which 
address 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, 
fuselage, and stabilizers.

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

Actions for Service Bulletin A310-53-2016--No Changes

    (g) For airplanes listed in Airbus Service Bulletin A310-53-
2016, Revision 5, dated December 7, 1992: 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), whichever 
occurs later, perform a defectoscope or rototest inspection to 
detect cracks in the area of frame 47 and frame 54, and install new 
doublers, in accordance with Airbus Service Bulletin A310-53-2016, 
Revision 5, dated December 7, 1992. Except as provided by paragraph 
(m) of this AD, if any discrepancy is found, prior to further 
flight, perform follow-on corrective actions, as applicable, in 
accordance with Airbus Service Bulletin A310-53-2016, Revision 5, 
dated December 7, 1992.

    Note 1:  Airplanes on which Airbus Modification 04980 is done in 
production are not affected by paragraph (g) of this AD.

Actions for Service Bulletin A310-53-2054, With Latest Optional 
Modification

    (h) For airplanes listed in Airbus Service Bulletin A310-53-
2054, Revision 2, dated May 22, 1990: Prior to the accumulation of 
12,000 total flight cycles, or within 1,000 flight cycles after 
January 20, 1999, whichever occurs later, and thereafter at 
intervals not to exceed 3,000 flight cycles, perform a visual 
inspection to detect cracks on frame 46 between the left- and right-
hand sides of stringers 21 and 22 on the forward and aft faces, in 
accordance with Airbus Service Bulletin A310-53-2054, Revision 2, 
dated May 22, 1990. If any crack is found, prior to further flight, 
repair in accordance with Airbus Service Bulletin A310-53-2054, 
Revision 2, dated May 22, 1990.

    Note 2:  Airplanes on which Airbus modification 05254 is done in 
production; or on which Airbus Service Bulletin A310-53-2019, 
Revision 2, dated May 22, 1990, or Revision 3, dated February 28, 
1991, is done in service; are not affected by paragraph (h) of this 
AD.

    (1) Prior to the effective date of this AD: Accomplishment of 
the repair required by paragraph (h) of this AD; or modification of 
the reinforcement angle runout in accordance with Airbus Service 
Bulletin A310-53-2019, Revision 2, dated May 22, 1990, or Revision 
3, dated February 28, 1991; terminates the repetitive inspection 
requirements of paragraph (h) of this AD.
    (2) On or after the effective date of this AD: Accomplishment of 
the repair required by paragraph (h) of this AD; or modification of 
the reinforcement angle runout in accordance with Airbus Service 
Bulletin A310-53-2019, Revision 3, dated February 28, 1991; 
terminates the repetitive inspection requirements of paragraph (h) 
of this AD.

Actions for Service Bulletin A310-53-2057--No Changes

    (i) For airplanes listed in Airbus Service Bulletin A310-53-
2057, Revision 1, dated April 30, 1992: Perform a visual inspection 
to detect cracks at the T-section connecting frame 50A to the beam 
between the left- and right-hand sides of frames 50 and 51, in 
accordance with Airbus Service Bulletin A310-53-2057, Revision 1, 
dated April 30, 1992. Perform the inspection at the time specified 
in paragraph (i)(1) or (i)(2) of this AD, as applicable. If any 
crack is found, prior to further flight, accomplish Airbus 
Modifications No. 4853 and No. 5273, in accordance with Airbus 
Service Bulletin A310-53-2057, Revision 1, dated April 30, 1992. 
Accomplishment of these modifications terminates the requirements of 
this paragraph.

    Note 3:  Airplanes on which Airbus modification 4853 is done are 
affected by paragraph (i) of this AD, except those airplanes on 
which Airbus Modification 5273 has been done or on which Airbus 
Service Bulletin A310-53-2011 has been done in service.

    (1) For the airplane having manufacturer's serial number (MSN) 
191: Prior to the accumulation of 24,000 total flight cycles, or 
within 1,000 flight cycles after January 20, 1999, whichever occurs 
later; and thereafter at intervals not to exceed 6,000 flight 
cycles.
    (2) For airplanes other than the airplane identified in 
paragraph (i)(1) of this AD: Prior to the accumulation of 12,000 
total flight cycles, or within 1,000 flight cycles after January 20, 
1999, whichever occurs later; and thereafter at intervals not to 
exceed 6,000 flight cycles.

Actions for Service Bulletin A310-53-2059--No Changes

    (j) For airplanes listed in Airbus Service Bulletin A310-53-
2059, Revision 1, dated January 4, 1996: Perform a visual inspection 
to detect cracks in the lower milled side panel at the lap joint 
with the upper side panel at frame 47 and stringer 22, left- and 
right-hand sides, in accordance with Airbus Service Bulletin A310-
53-2059, Revision 1, dated January 4, 1996. Perform the inspection 
at the time specified in paragraph (j)(1) or (j)(2) of this AD, as 
applicable. Except as provided by paragraph (m) of this AD, if any 
crack is found, prior to further flight, repair in accordance with 
Airbus Service Bulletin A310-53-2059, Revision 1, dated January 4, 
1996. Thereafter, repeat the inspections at intervals not to exceed 
9,000 flight cycles, or accomplish Airbus Modification 5997 (Airbus 
Service Bulletin A310-53-2058). Accomplishment of either the repair 
or Airbus Modification 5997 constitutes terminating action for the 
repetitive inspections required by this paragraph.

    Note 4:  Airplanes on which Airbus Modification 5997 has been 
done completely in production, or on which Airbus Service Bulletin 
A310-53-2058 has been done in service, are not affected by the 
actions in paragraph (j) of this AD.

    (1) For Model A310-200 series airplanes, accomplish the 
inspection at the time specified in paragraph (j)(1)(i) or 
(j)(1)(ii) of this AD, as applicable.
    (i) For airplanes that have accumulated less than 20,000 total 
flight cycles as of January 20, 1999: Prior to the accumulation of 
18,000 total flight cycles, or within 2,000 flight cycles after 
January 20, 1999, whichever occurs later.
    (ii) For airplanes that have accumulated 20,000 or more total 
flight cycles as of January 20, 1999: Within 1,000 flight cycles 
after January 20, 1999.
    (2) For Model A310-300 series airplanes, accomplish the 
inspection at the time

[[Page 45]]

specified in paragraph (j)(2)(i) or (j)(2)(ii) of this AD, as 
applicable.
    (i) For airplanes that have accumulated less than 19,700 total 
flight cycles as of January 20, 1999: Prior to the accumulation of 
18,000 total flight cycles, or within 1,700 flight cycles after 
January 20, 1999, whichever occurs later.
    (ii) For airplanes that have accumulated 19,700 or more total 
flight cycles as of January 20, 1999: Within 850 flight cycles after 
January 20, 1999.

Actions for Service Bulletin A310-55-2002--No Changes

    (k) For airplanes listed in Airbus Service Bulletin A310-55-
2002, Revision 4, dated April 28, 1989: Prior to the accumulation of 
12,000 total flight cycles, or within 1,000 flight cycles after 
January 20, 1999, whichever occurs later, perform an eddy current 
inspection to detect cracks on the upper integral part adjacent to 
the rear attach fittings on the horizontal stabilizer, and modify 
the horizontal stabilizer, in accordance with Airbus Service 
Bulletin A310-55-2002, Revision 4, dated April 28, 1989. Except as 
provided by paragraph (m) of this AD, if any discrepancy is found, 
prior to further flight, perform follow-on corrective actions, as 
applicable, in accordance with Airbus Service Bulletin A310-55-2002, 
Revision 4, dated April 28, 1989.

Actions for Service Bulletin A310-57-2039--No Changes

    (l) For airplanes listed in Airbus Service Bulletin A310-57-
2039, dated September 24, 1990: Perform either an eddy current or 
visual inspection to detect cracks on the left and right vertical 
posts, numbers 1 through 5 inclusive, in the wing center box at 
frame 40/41, in accordance with Airbus Service Bulletin A310-57-
2039, dated September 24, 1990. Perform the inspection at the time 
specified in paragraph (l)(1) or (l)(2) of this AD, as applicable. 
Except as provided by paragraph (m) of this AD, if any crack is 
found, prior to further flight, accomplish the modification 
specified in Airbus Service Bulletin A310-57-2041, dated September 
24, 1990, in accordance with Airbus Service Bulletin A310-57-2039, 
dated September 24, 1990.

    Note 5:  Airplanes on which Airbus Modification 04977 has been 
done in production are not affected by the actions specified in 
paragraph (l) of this AD.

    (1) For airplanes on which Airbus Modification 7541/S7973 
(reference Airbus Service Bulletin A310-57-2041) has not been 
accomplished: Inspect prior to the accumulation of 21,000 total 
flight cycles, or within 1,000 flight cycles after January 20, 1999, 
whichever occurs later; and thereafter at intervals not to exceed 
4,200 flight cycles (for a visual inspection), or 7,500 flight 
cycles (for an eddy current inspection).
    (2) For airplanes on which Airbus Modification 7541/S7973 
(reference Airbus Service Bulletin A310-57-2041) has been 
accomplished: Inspect at the time specified in the graph contained 
in NOTE 1 of paragraph 1.A.(2) of Airbus Service Bulletin A310-57-
2039, dated September 24, 1990, or within 1,000 flight cycles after 
January 20, 1999, whichever occurs later; and thereafter at 
intervals not to exceed 5,000 flight cycles (for a visual 
inspection), or 8,600 flight cycles (for an eddy current 
inspection).

Exception to Certain Service Bulletin Repairs

    (m) If any crack is found during any inspection required by 
paragraph (g), (j), (k), or (l) of this AD, and the applicable 
service bulletin specifies to contact Airbus for an appropriate 
action: Prior to further flight, repair in accordance with a method 
approved by either the Manager, International Branch, ANM-116, or 
the DGAC (or its delegated agent), or EASA (or its delegated agent).

New Requirements of This AD: Actions

Actions for Service Bulletin A310-55-2004

    (n) For airplanes listed in Airbus Mandatory Service Bulletin 
A310-55-2004, Revision 05, dated October 13, 2006: At the applicable 
time specified in paragraph (n)(1) or (n)(2) of this AD, do a high 
frequency eddy current inspection for cracking of the doubler plate 
edge, the rear spar area, and specified fastener holes in the top 
skin chordwise splice along the contour of the steel doubler between 
ribs 3 and 4 on the left- and right-hand center and side boxes on 
the horizontal stabilizer, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A310-55-2004, 
Revision 05, dated October 13, 2006. If any cracking is found, 
before further flight, repair in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A310-55-2004, 
Revision 05, dated October 13, 2006; except where this service 
bulletin specifies to contact Airbus, before further flight, repair 
in accordance with a method approved by either the Manager, 
International Branch, ANM-116, FAA, or EASA (or its delegated 
agent). Thereafter, repeat the inspections at intervals not to 
exceed 9,700 flight cycles or 19,500 flight hours, whichever occurs 
first; except as required by paragraph (o) of this AD for the rear 
spar area.

    Note 6:  Airplanes on which Airbus Modification 06070 has been 
done in production are not affected by the actions specified in 
paragraph (l) of this AD.

    (1) For airplanes on which Airbus Service Bulletin A310-55-2002 
was accomplished prior to the accumulation of 6,000 total flight 
cycles on the airplane; and for airplanes having MSN 311 through 400 
inclusive on which Airbus Modification 4933 was accomplished during 
production: Do the inspection at the later of the compliance times 
specified in paragraphs (l)(1)(i) and (l)(1)(ii) of this AD.
    (i) Prior to the accumulation of 14,400 total flight cycles or 
28,500 total flight hours, whichever occurs first.
    (ii) Within 1,500 flight cycles or 18 months after the effective 
date of this AD, whichever occurs first.
    (2) For airplanes on which Airbus Service Bulletin A310-55-2002 
was accomplished on or after the accumulation of 6,000 total flight 
cycles: Do the inspection at the later of the times specified in 
paragraphs (l)(2)(i) and (l)(2)(ii) of this AD.
    (i) Within 9,700 flight cycles or 19,500 flight hours after 
accomplishing the modification, whichever occurs first.
    (ii) Within 1,500 flight cycles or 18 months after the effective 
date of this AD, whichever occurs first.
    (o) For airplanes on which the initial inspection required by 
paragraph (n) of this AD has been done and on which a repair was 
installed at fastener position A in accordance with Airbus Service 
Bulletin A310-55-2002: At the later of the times specified in 
paragraphs (o)(1) and (o)(2) of this AD, do a high frequency eddy 
current inspection for cracking of the rear spar area as specified 
in paragraph (n) of this AD, and repeat the high frequency eddy 
current inspection of the rear spar area thereafter at intervals not 
to exceed 4,800 flight cycles or 9,700 flight hours, whichever 
occurs first.
    (1) Within 4,800 flight cycles or 9,700 flight hours, whichever 
occurs first, after doing the repair in accordance with Airbus 
Service Bulletin A310-55-2002.
    (2) Within 400 flight cycles or 800 flight hours, whichever 
occurs first, after the effective date of this AD.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (p) Actions accomplished before the effective date of this AD in 
accordance with Airbus Service Bulletin A310-55-2004, Revision 2, 
dated February 7, 1991; Revision 3, dated April 16, 1997; and 
Revision 04, dated April 17, 2001; are acceptable for compliance 
with the corresponding actions specified in paragraph (n) of this 
AD.

FAA AD Differences

    Note 7: This AD differs from the MCAI and/or service information 
as follows: No Differences.

Other FAA AD Provisions

    (q) 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 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. AMOCs approved 
previously in accordance with AD 98-26-01, amendment 39-10942, 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

[[Page 46]]

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

    (r) Refer to MCAI EASA Airworthiness Directive 2007-0053R3, 
dated December 17, 2009, and the service bulletins listed in Table 1 
of this AD, for related information.

                  Table 1--Related Service Information
------------------------------------------------------------------------
        Service bulletin               Revision              Date
------------------------------------------------------------------------
Airbus Mandatory Service          05................  October 13, 2006.
 Bulletin A310-55-2004.
Airbus Service Bulletin A310-53-  5.................  December 7, 1992.
 2016.
Airbus Service Bulletin           3.................  February 28, 1991.
 A310[dash]53[dash]2019.
Airbus Service Bulletin A310-53-  2.................  May 22, 1990.
 2054.
Airbus Service Bulletin A310-53-  1.................  April 30, 1992.
 2057.
Airbus Service Bulletin A310-53-  1.................  January 4, 1996.
 2059.
Airbus Service Bulletin A310-55-  4.................  April 28, 1989.
 2002.
Airbus Service Bulletin A310-57-  Original..........  September 24,
 2039.                                                 1990.
Airbus Service Bulletin A310-57-  Original..........  September 24,
 2041.                                                 1990.
------------------------------------------------------------------------


    Issued in Renton, Washington on December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-32983 Filed 12-30-10; 8:45 am]
BILLING CODE 4910-13-P


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