```

[Federal Register: July 13, 2010 (Volume 75, Number 133)]
[Proposed Rules]               
[Page 39863-39868]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13jy10-22]                         

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

========================================================================

[[Page 39863]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-0680; Directorate Identifier 2008-NM-195-AD]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A310 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to adopt a new airworthiness directive (AD) for the 
products listed above that would supersede an existing AD. 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: Analysis performed in the frame 
of the Extended Service Goal has led Airbus to modify the inspection 
programme [modification of thresholds, intervals and associated 
configurations] which is currently required by DGAC (Direction 
G[eacute]n[eacute]rale de l'Aviation Civile) France AD F-2005-001. This 
modified inspection programme is necessary to detect and prevent damage 
associated with a structural fatigue phenomenon of the rear spar 
internal angle and the tee fitting located in the centre wing box. This 
condition, if not corrected, could affect the structural integrity of 
the centre wing box. The unsafe condition is reduced structural 
integrity of the wings. 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 August 27, 2010.

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

Examining the AD Docket

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

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; 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-2010-0680; 
Directorate Identifier 2008-NM-195-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 have lengthened the 30-day comment period for proposed ADs that 
address MCAI originated by aviation authorities of other countries to 
provide adequate time for interested parties to submit comments. The 
comment period for these proposed ADs is now typically 45 days, which 
is consistent with the comment period for domestic transport ADs.
    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 April 20, 2006, we issued AD 2006-09-05, Amendment 39-14575 (71 
FR 25921, May 3, 2006). That AD required actions intended to address an 
unsafe condition on the products listed above.
    Since we issued AD 2006-09-05, the manufacturer has modified the 
inspection program currently required by AD 2006-09-05 by reducing 
certain compliance times. The European Aviation Safety Agency (EASA), 
which is the Technical Agent for the Member States of the European 
Community, has issued EASA Airworthiness Directive 2008-0187, dated 
October 10, 2008 (referred to after this as ``the MCAI''), to correct 
an unsafe condition for the specified products. The MCAI states:

    Analysis performed in the frame of the Extended Service Goal has 
led Airbus to modify the inspection programme [modification of 
thresholds, intervals and associated configurations] which is 
currently required by DGAC (Direction G[eacute]n[eacute]rale de 
l'Aviation Civile) France AD F-2005-001 [which corresponds to FAA AD 
2006-09-05].
    This modified inspection programme is necessary to detect and 
prevent damage associated with a structural fatigue phenomenon of 
the rear spar internal angle and the tee fitting located in the 
centre wing box. This condition, if not corrected, could affect the 
structural integrity of the centre wing box.

[[Page 39864]]

    For the reason stated above, this new EASA AD retains the 
requirements of DGAC France AD F-2005-001, which is superseded, and 
refers to the latest revision of Airbus Service Bulletin (SB) A310-
57-2047.

The unsafe condition is reduced structural integrity of the wings. This 
AD retains the requirements of AD 2006-09-05, but with certain reduced 
compliance times. The required actions include doing repetitive 
rotating probe inspections for any crack of the rear spar internal 
angle and the left and right sides of the tee fitting, and doing 
related investigative/corrective actions if necessary. The actions also 
include modifying the holes in the internal angle and tee fitting by 
cold expansion. You may obtain further information by examining the 
MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletin A310-57-2047, Revision 08, dated 
July 2, 2009; and Mandatory Service Bulletin A310-57-2035, Revision 10, 
dated March 25, 2008. The actions described in this service information 
are intended to correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

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

Differences Between This AD and the MCAI or Service Information

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

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 66 products of U.S. registry.
    The actions that are required by AD 2006-09-05 and retained in this 
proposed AD take up to 600 work-hours per product, at an average labor 
rate of $85 per work hour. Required parts cost up to $38,900 per 
product. Based on these figures, the estimated cost of the currently 
required actions is up to $89,900 per product.
    This new AD adds no new costs to affected operators; the 
manufacturer has modified the inspection program currently required by 
AD 2006-09-05, this proposed AD reduces the compliance times required 
by the existing AD.

Authority for This Rulemaking

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

Regulatory Findings

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

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-14575 (71 FR 
25921, May 3, 2006) and adding the following new AD:

Airbus: Docket No. FAA-2010-0680; Directorate Identifier 2008-NM-
195-AD.

Comments Due Date

    (a) We must receive comments by August 27, 2010.

Affected ADs

    (b) This AD supersedes AD 2006-09-05, Amendment 39-14575. This 
AD also affects certain requirements of AD 98-26-01, Amendment 39-
10942.

Applicability

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

Subject

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

Reason

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

    Analysis performed in the frame of the Extended Service Goal has 
led Airbus to modify the inspection programme [modification of 
thresholds, intervals and associated configurations] which is 
currently required by DGAC (Direction G[eacute]n[eacute]rale de 
l'Aviation Civile) France AD F-2005-001 [which corresponds to FAA AD 
2006-09-05].
    This modified inspection programme is necessary to detect and 
prevent damage associated with a structural fatigue phenomenon of 
the rear spar internal angle and the tee fitting located in the 
centre wing box. This condition, if not corrected, could affect the 
structural integrity of the centre wing box.

The unsafe condition is reduced structural integrity of the wings.

[[Page 39865]]

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 2006-09-05 MODIFICATION

    (g) For all airplanes except those that are modified by Airbus 
Modifications 06672S6812, 06673S6813, and 07387S7974 in production: 
Within 60 months after June 7, 2006 (the effective date of AD 2006-
09-05), modify the holes in the internal angle and tee fitting and 
do all applicable related investigative and corrective actions by 
accomplishing all the actions specified in the Accomplishment 
Instructions of Airbus Service Bulletin A310-57-2035, Revision 08, 
dated September 19, 2005; or Airbus Mandatory Service Bulletin A310-
57-2035, Revision 10, dated March 25, 2008; except as required by 
paragraph (h) of this AD. Do all applicable related investigative 
and corrective actions before further flight. As of the effective 
date of this AD, use only Airbus Mandatory Service Bulletin A310-57-
2035, Revision 10, dated March 25, 2008.

Contact the FAA

    (h) Where the service information specified in Table 1 of this 
AD specifies to contact the manufacturer if certain cracks are 
found, before further flight, repair those conditions according to a 
method approved by either the Manager, International Branch, ANM-
116, Transport Airplane Directorate, FAA; or the Direction 
G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or its delegated 
agent); or EASA (or its delegated agent).

                      Table 1--Service Information
------------------------------------------------------------------------
           Document               Revision               Date
------------------------------------------------------------------------
Airbus Mandatory Service                 10  March 25, 2008.
 Bulletin A310-57-2035.
Airbus Service Bulletin A310-            08  September 19, 2005.
 57-2035.
------------------------------------------------------------------------

Actions Accomplished According to Previous Issues of Airbus Service 
Bulletin A310-57-2035

    (i) Actions accomplished before June 7, 2006, in accordance with 
the service information specified in Table 2 of this AD, are 
considered acceptable for compliance with the corresponding actions 
specified in paragraph (g) of this AD.

        Table 2--Previous Issues of Service Bulletin A310-57-2035
------------------------------------------------------------------------
           Document               Revision               Date
------------------------------------------------------------------------
Airbus Service Bulletin A310-             1  October 13, 1989.
 57-2035.
Airbus Service Bulletin A310-             2  February 26, 1990.
 57-2035.
Airbus Service Bulletin A310-             3  May 23, 1990.
 57-2035.
Airbus Service Bulletin A310-             4  April 15, 1992.
 57-2035.
Airbus Service Bulletin A310-             5  May 27, 1992.
 57-2035.
Airbus Service Bulletin A310-             6  March 8, 1994.
 57-2035.
Airbus Service Bulletin A310-             7  April 17, 1996.
 57-2035.
------------------------------------------------------------------------

NEW REQUIREMENTS OF THIS AD--REVISED COMPLIANCE TIMES FOR INSPECTIONS 
REQUIRED BY AD 2006-09-05

Initial and Repetitive Inspections of the Rear Spar Internal Angle

    (j) For airplanes on which an inspection of the rear spar 
internal angle has not been done in accordance with Airbus Service 
Bulletin A310-57-2047 as of the effective date of this AD: At the 
later of the times specified in paragraphs (j)(1) and (j)(2) of this 
AD, do a rotating probe inspection for any crack of the rear spar 
internal angle located in the center wing box and do all applicable 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2047, 
Revision 08, dated July 2, 2009; except as required by paragraphs 
(n) and (o) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Repeat the inspection 
thereafter at the applicable time specified in Table 4 of this AD. 
Certain compliance times are applicable to short range use, average 
flight time (AFT) equal to or less than 4 hours, or long range use, 
AFT exceeding 4 hours.

    Note 1:  To establish the AFT, divide the accumulated flight 
time (counted from the take-off up to the landing) by the number of 
accumulated flight cycles. This gives the average flight time per 
flight cycle.

    (1) Within the applicable time specified in Table 3 of this AD.
    (2) Within the applicable time specified in paragraph (j)(2)(i), 
(j)(2)(ii), or (j)(2)(iii) of this AD:
    (i) For A310-203, -204, -221, and -222 airplanes: Within 700 
flight cycles or 1,500 flight hours after the effective date of this 
AD, whichever occurs first.
    (ii) For A310-304, -322, -324, and -325 short range airplanes: 
Within 700 flight cycles or 1,900 flight hours after the effective 
date of this AD, whichever occurs first.
    (iii) For A310-304, -322, -324, and -325 long range airplanes: 
Within 500 flight cycles or 2,500 flight hours after the effective 
date of this AD, whichever occurs first.

               Table 3--Initial Inspection Internal Angle
------------------------------------------------------------------------

------------------------------------------------------------------------
   Model and configuration     Compliance time (whichever occurs first)
------------------------------------------------------------------------
A310-203, -204, -221, and -   Before the            Before the
 222 airplanes on which Mod    accumulation of       accumulation of
 6672S6812 and Mod 7387S7974   9,200 total flight    18,500 total flight
 are not done.                 cycles.               hours.
A310-203, -204, -221, and -   Before the            Before the
 222 airplanes on which Mod    accumulation of       accumulation of
 6672S6812 and Mod 7387S7974   19,800 total flight   39,600 total flight
 are done in production.       cycles.               hours.

[[Page 39866]]

A310-203, -204, -221, and -   Within 19,800 flight  Within 39,600 flight
 222 airplanes on which Mod    cycles after the      hours after the
 6672S6812 and Mod 7387S7974   effective date of     effective date of
 are done in accordance with   this AD.              this AD.
 Airbus Service Bulletin
 A310-57-2035 and before the
 accumulation of 6,200 total
 flight cycles and 12,500
 total flight hours.
A310-203, -204, -221, and -   Within 8,200 flight   Within 16,400 flight
 222 airplanes on which Mod    cycles after the      hours after the
 6672S6812 and Mod 7387S7974   effective date of     effective date of
 are done in accordance with   this AD.              this AD.
 Airbus Service Bulletin
 A310-57-2035 and are not
 done before the
 accumulation of 6,200 total
 flight cycles and 12,500
 total flight hours.
A310-304, -322, -324, and -   Before the            Before the
 325 short range airplanes     accumulation of       accumulation of
 on which Mod 6672S6812 and    7,500 total flight    21,100 total flight
 Mod 7387S7974 are not done.   cycles.               hours.
A310-304, -322, -324, and -   Before the            Before the
 325 long range airplanes on   accumulation of       accumulation of
 which Mod 6672S6812 and Mod   5,300 total flight    26,900 total flight
 7387S7974 are not done.       cycles.               hours.
A310-304, -322, -324, and -   Before the            Before the
 325 short range airplanes     accumulation of       accumulation of
 on which Mod 6672S6812 and    15,900 total flight   44,700 total flight
 Mod 7387S7974 are done.       cycles.               hours.
A310-304, -322, -324, and -   Before the            Before the
 325 long range airplanes on   accumulation of       accumulation of
 which Mod 6672S6812 and Mod   11,300 total flight   56,900 total flight
 7387S7974 are done in         cycles.               hours.
 production.
A310-304, -322, -324, and -   Within 15,900 flight  Within 44,700 flight
 325 short range airplanes     cycles after the      hours after the
 on which Mod 6672S6812 and    effective date of     effective date of
 Mod 7387S7974 are done in     this AD.              this AD.
 accordance with Airbus
 Service Bulletin A310-57-
 2035 and before the
 accumulation of 4,700 total
 flight cycles and 13,100
 total flight hours.
A310-304, -322, -324, and -   Within 8,500 flight   Within 23,800 flight
 325 short range airplanes     cycles after the      hours after the
 on which Mod 6672S6812 and    effective date of     effective date of
 Mod 7387S7974 are done in     this AD.              this AD.
 accordance with Airbus
 Service Bulletin A310-57-
 2035 and not done before
 the accumulation of 4,700
 total flight cycles and
 13,100 total flight hours.
A310-304, -322, -324, and -   Within 11,300 flight  Within 56,900 flight
 325 long range airplanes on   cycles after the      hours after the
 which Mod 6672S6812 and Mod   effective date of     effective date of
 7387S7974 are done in         this AD.              this AD.
 accordance with Airbus
 Service Bulletin A310-57-
 2035 before the
 accumulation of 3,300 total
 flight cycles and 16,700
 total flight hours.
A310-304, -322, -324, and -   Within 6,000 flight   Within 30,300 flight
 325 long range airplanes on   cycles after the      hours after the
 which Mod 6672S6812 and Mod   effective date of     effective date of
 7387S7974 are done in         this AD.              this AD.
 accordance with Airbus
 Service Bulletin A310-57-
 2035 and not done before
 the accumulation of 3,300
 total flight cycles and
 16,700 total flight hours.
------------------------------------------------------------------------

                      Table 4--Repetitive Intervals
------------------------------------------------------------------------
        Model and configuration              Interval (not to exceed)
------------------------------------------------------------------------
A310-203, -204, -221, and -222           Within 7,200 flight cycles or
 airplanes.                               14,400 flight hours, whichever
                                          occurs first.
A310-304, -322, -324, and -325 short     Within 6,800 flight cycles or
 range airplanes.                         19,100 flight hours, whichever
                                          occurs first.
A310-304, -322, -324, and -325 long      Within 4,800 flight cycles or
 range airplanes.                         24,300 flight hours, whichever
                                          occurs first.
------------------------------------------------------------------------

    (k) For airplanes on which an inspection of the rear spar 
internal angle has been done in accordance with Airbus Service 
Bulletin A310-57-2047 as of the effective date of this AD: At the 
applicable time specified in paragraphs (k)(1), (k)(2), and (k)(3) 
of this AD, do a rotating probe inspection for any crack of the rear 
spar internal angle located in the center wing box and do all 
applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A310-57-2047, Revision 08, dated July 2, 2009; except as 
required by paragraphs (n) and (o) of this AD. Do all applicable 
related investigative and corrective actions before further flight. 
Repeat the inspection thereafter at the applicable time specified in 
Table 4 of this AD. Certain compliance times are applicable to short 
range use, AFT equal to or less than 4 hours, or long range use, AFT 
exceeding 4 hours.
    (1) For A310-203, -204, -221, and -222 airplanes: At the earlier 
of the times specified in paragraphs (k)(1)(i) and (k)(1)(ii) of 
this AD.
    (i) Within 7,940 flight cycles or 15,880 flight hours after the 
most recent inspection, whichever occurs first.
    (ii) At the later of the times specified in paragraphs 
(k)(1)(ii)(A) and (k)(1)(ii)(B) of this AD.
    (A) Within the applicable interval specified in Table 4 of this 
AD.
    (B) Within 740 flight cycles or 1,480 flight hours after the 
effective date of this AD, whichever occurs first.
    (2) For A310-304, -322, -324, and -325 short range airplanes: At 
the later of the times

[[Page 39867]]

specified in paragraphs (k)(2)(i) and (k)(2)(ii) of this AD.
    (i) Within the applicable interval specified in Table 4 of this 
AD.
    (ii) Within 700 flight cycles or 1,900 flight hours after the 
effective date of this AD, whichever occurs first.
    (3) For A310-304, -322, -324, and -325 long range airplanes: At 
the later of the times specified in paragraphs (k)(3)(i) and 
(k)(3)(ii) of this AD.
    (i) Within the applicable interval specified in Table 4 of this 
AD.
    (ii) Within 500 flight cycles or 2,500 flight hours after the 
effective date of this AD, whichever occurs first.

Initial and Repetitive Inspections of the Tee Fitting

    (l) For airplanes on which an inspection of the left and right 
sides of the tee fitting has not been done in accordance with Airbus 
Service Bulletin A310-57-2047 as of the effective date of this AD: 
At the later of the times specified in paragraphs (l)(1) and (l)(2) 
of this AD, do a rotating probe inspection for any crack of the left 
and right sides of the tee fitting, and do all applicable related 
investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2047, 
Revision 08, dated July 2, 2009; except as required by paragraphs 
(n) and (o) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Repeat the inspection 
thereafter at the applicable time specified in Table 6 of this AD. 
Certain compliance times are applicable to short range use, AFT 
equal to or less than 4 hours, or long range use, AFT exceeding 4 
hours.
    (1) Within the applicable time specified in Table 5 of this AD.
    (2) Within the applicable time in paragraph (l)(2)(i), 
(l)(2)(ii), or (l)(2)(iii) of this AD.
    (i) For A310-203, -204, -221, and -222 airplanes: Within 800 
flight cycles or 1,600 flight hours, whichever occurs first.
    (ii) For A310-304, -322, -324, and -325 short range airplanes: 
Within 800 flight cycles or 2,200 flight hours, whichever occurs 
first.
    (iii) For A310-304, -322, -324, and -325 long range airplanes: 
Within 600 flight cycles or 3,100 flight hours, whichever occurs 
first.

                 Table 5--Initial Inspection Tee Fitting
------------------------------------------------------------------------

------------------------------------------------------------------------
   Model and configuration     Compliance time (whichever occurs first)
------------------------------------------------------------------------
A310-203, -204, -221, and -   Before the            Within 28,700 flight
 222 airplanes on which Mod    accumulation of       hours after the
 6673S6813 is not done.        14,300 flight         effective date of
                               cycles.               this AD.
A310-203, -204, -221, and -   Before the            Before the
 222 airplanes on which Mod    accumulation of       accumulation of
 6673S6813 is done in          17,500 total flight   35,000 total flight
 production.                   cycles.               hours.
A310-203, -204, -221, and -   Within 17,500 flight  Within 35,000 flight
 222 airplanes on which Mod    cycles after the      hours after the
 6673S6813 is done in          effective date of     effective date of
 accordance with Airbus        this AD.              this AD.
 Service Bulletin A310-57-
 2035 and before the
 accumulation of 8,100 total
 flight cycles and 16,200
 total flight hours.
A310-203, -204, -221, and -   Within 9,600 flight   Within 19,200 flight
 222 airplanes on which Mod    cycles after the      hours after the
 6673S6813 is done in          effective date of     effective date of
 accordance with Airbus        this AD.              this AD.
 Service Bulletin A310-57-
 2035 and not before the
 accumulation of 8,100 total
 flight cycles and 16,200
 total flight hours.
A310-304, -322, -324, and -   Within 10,800 flight  Within 30,400 flight
 325 short range airplanes     cycles after the      hours after the
 on which Mod 6673S6813 is     effective date of     effective date of
 not done.                     this AD.              this AD.
A310-304, -322, -324, and -   Before the            Before the
 325 long range airplanes on   accumulation of       accumulation of
 which Mod 6673S6813 is not    8,500 total flight    42,800 total flight
 done.                         cycles.               hours.
A310-304, -322, -324, and -   Before the            Before the
 325 short range airplanes     accumulation of       accumulation of
 on which Mod 6673S6813 is     13,100 total flight   36,700 total flight
 done in production.           cycles.               hours.
A310-304, -322, -324, and -   Before the            Before the
 325 long range airplanes on   accumulation of       accumulation of
 which Mod 6673S6813 is done   10,300 total flight   51,600 total flight
 in production.                cycles.               hours.
A310-304, -322, -324, and -   Within 13,100 flight  Within 36,700 flight
 325 short range airplanes     cycles after the      hours after the
 on which Mod 6673S6813 is     effective date of     effective date of
 done in accordance with       this AD.              this AD.
 Airbus Service Bulletin
 A310-57-2035 and before the
 accumulation of 5,800 total
 flight cycles and 16,400
 total flight hours.
A310-304, -322, -324, and -   Within 7,400 flight   Within 20,900 flight
 325 short range airplanes     cycles after the      hours after the
 on which Mod 6673S6813 is     effective date of     effective date of
 done in accordance with       this AD.              this AD.
 Airbus Service Bulletin
 A310-57-2035 and not before
 the accumulation of 5,800
 total flight cycles and
 16,400 total flight hours.
A310-304, -322, -324, and -   Within 10,300 flight  Within 51,600 flight
 325 long range airplanes on   cycles after the      hours after the
 which Mod 6673S6813 is done   effective date of     effective date of
 in accordance with Airbus     this AD.              this AD.
 Service Bulletin A310-57-
 2035 and before the
 accumulation of 4,600 total
 flight cycles and 23,100
 total flight hours.
A310-304, -322, -324, and -   Within 6,000 flight   Within 30,300 flight
 325 long range airplanes on   cycles after the      hours after the
 which Mod 6673S6813 is done   effective date of     effective date of
 in accordance with Airbus     this AD.              this AD.
 Service Bulletin A310-57-
 2035 and not before the
 accumulation of 4,600 total
 flight cycles and 23,100
 total flight hours.
------------------------------------------------------------------------

[[Page 39868]]

                      Table 6--Repetitive Intervals
------------------------------------------------------------------------
        Model and configuration              Interval (not to exceed)
------------------------------------------------------------------------
A310-203, -204, -221, and -222           9,100 flight cycles or 18,300
 airplanes.                               flight hours, whichever occurs
                                          first.
A310-304, -322, -324, and -325 short     7,300 flight cycles or 20,400
 range airplanes.                         flight hours, whichever occurs
                                          first.
A310-304, -322, -324, and -325 long      5,900 flight cycles or 29,600
 range airplanes.                         flight hours, whichever occurs
                                          first
------------------------------------------------------------------------

     (m) For airplanes on which an inspection of the rear left and 
right sides of the tee fitting has been done in accordance with 
Airbus Service Bulletin A310-57-2047 as of the effective date of 
this AD: At the applicable time specified in paragraphs (m)(1) or 
(m)(2) of this AD, do a rotating probe inspection for any crack of 
the left and right sides of the tee fitting, and do all applicable 
related investigative and corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2047, 
Revision 08, dated July 2, 2009; except as required by paragraphs 
(n) and (o) of this AD. Do all applicable related investigative and 
corrective actions before further flight. Repeat the inspection 
thereafter at the applicable time specified in Table 6 of this AD. 
Certain compliance times are applicable to short range use, AFT 
equal to or less than 4 hours, or long range use, AFT exceeding 4 
hours.
    (1) For A310-203, -204, -221, and -222 airplanes: At the earlier 
of the times specified in paragraphs (m)(1)(i) and (m)(1)(ii) of 
this AD.
    (i) Within 10,800 flight cycles or 17,400 flight hours after the 
most recent inspection, whichever occurs first.
    (ii) At the later of the times specified in paragraphs 
(m)(1)(ii)(A) and (m)(1)(ii)(B) of this AD.
    (A) Within the applicable interval specified in Table 6 of this 
AD.
    (B) Within 700 flight cycles or 1,500 flight hours after the 
effective date of this AD, whichever occurs first.
    (2) For A310-304, -322, -324, and -325 airplanes: At the later 
of the times specified in paragraphs (m)(2)(i) and (m)(2)(ii) of 
this AD.
    (i) Within the applicable interval specified in Table 6 of this 
AD.
    (ii) Within 700 flight cycles or 1,900 flight hours after the 
effective date of this AD, whichever occurs first.

Contact the FAA

    (n) Where Airbus Service Bulletin A310-57-2047, Revision 08, 
dated July 2, 2009, specifies to contact the manufacturer if certain 
cracks are found, before further flight, repair those conditions 
according to a method approved by either the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or 
its delegated agent).

No Reporting Required

    (o) Although Airbus Service Bulletin A310-57-2047, Revision 06, 
dated July 13, 2004; and Revision 08, dated July 2, 2009; specify to 
submit certain information to the manufacturer, this AD does not 
include that requirement.
    (p) Actions accomplished before the effective date of this AD in 
accordance with Airbus Mandatory Service Bulletin A310-57-2035, 
Revision 09, dated September 27, 2007, are considered acceptable for 
compliance with the corresponding actions specified in paragraph (g) 
of this AD.
    (q) Actions accomplished before the effective date of this AD in 
accordance with the service information specified in Table 7 of this 
AD, are considered acceptable for compliance with the corresponding 
actions specified in paragraphs (j) through (m) of this AD.

        Table 7--Previous Issues of Service Bulletin A310-57-2047
------------------------------------------------------------------------
          Document               Revision                Date
------------------------------------------------------------------------
Airbus Service Bulletin                   03  November 26, 1997.
 A310[dash]57[dash]2047.
Airbus Service Bulletin A310-             04  March 5, 1999.
 57-2047.
Airbus Service Bulletin A310-             05  August 3, 2000.
 57-2047.
Airbus Service Bulletin A310-             06  July 13, 2004.
 57-2047.
Airbus Service Bulletin A310-             07  March 14, 2008.
 57-2047.
------------------------------------------------------------------------

Related AD

    (r) Accomplishing a rotating probe inspection of the rear spar 
internal angle and the tee fitting in accordance with Airbus Service 
Bulletin A310-57-2047, Revision 08, dated July 2, 2009, or a service 
bulletin listed in Table 7 of this AD, terminates the requirements 
specified in paragraph (o) of AD 98-26-01.

FAA AD Differences

    Note 2:  This AD differs from the MCAI and/or service 
information as follows:

Although the MCAI or service information tells you to contact the 
manufacturer for repair information, paragraph (n) of this AD 
requires that you contact the FAA or EASA (or its delegated agent) 
instead. Although the MCAI or service information tells you to 
submit information to the manufacturer, paragraph (o) of this AD 
specifies that such submittal is not required.

Other FAA AD Provisions

    (s) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information to ATTN: Dan 
Rodina, Aerospace Engineer, International Branch, ANM-116, FAA, 
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, 
Washington 98055-4056; 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.
    (2) AMOCs approved previously in accordance with AD 2006-09-05, 
Amendment 39-14575, are approved as AMOCs for the corresponding 
provisions of this AD.
    (3) 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

    (t) Refer to MCAI EASA Airworthiness Directive 2008-0187, dated 
October 10, 2008; and Airbus Service Bulletins A310-57-2047, 
Revision 08, dated July 2, 2009; and Airbus Mandatory Service 
Bulletin A310-57-2035, Revision 10, dated March 25, 2008; for 
related information.

    Issued in Renton, Washington, on June 30, 2010.
Todd G. Dixon,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-17061 Filed 7-12-10; 8:45 am]
BILLING CODE 4910-13-P
```