AD 2006-09-05

[Federal Register Volume 71, Number 85 (Wednesday, May 3, 2006)]
[Rules and Regulations]
[Pages 25921-25924]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 06-4052]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2006-23870; Directorate Identifier 2005-NM-022-AD; 
Amendment 39-14575; AD 2006-09-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A310-200 and -300 Series 
Airplanes

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

ACTION: Final rule.

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SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all 
Airbus Model A310-200 and -300 series airplanes. This AD requires 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. This AD 
also requires modifying the holes in the internal angle and tee fitting 
by cold expansion. This AD results from full-scale fatigue tests, which 
revealed cracks in the lower rear spar internal angle, and tee fitting. 
We are issuing this AD to detect and correct fatigue cracks of the rear 
spar internal angle and tee fitting, which could lead to the rupture of 
the internal angle, tee fitting, and rear spar, and consequent reduced 
structural integrity of the wings.

DATES: This AD becomes effective June 7, 2006.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in the AD as of June 7, 2006.

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a> or in person at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Nassif Building, 
Room PL-401, Washington, DC.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this AD.

FOR FURTHER INFORMATION CONTACT: Tim Backman, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2797; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION:

Examining the Docket

    You may examine the airworthiness directive (AD) docket on the 
Internet at

[[Page 25922]]

<a href="http://dms.dot.gov">http://dms.dot.gov</a> or in person at the Docket Management Facility 
office between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The Docket Management Facility office (telephone (800) 647-
5227) is located on the plaza level of the Nassif Building at the 
street address stated in the ADDRESSES section.

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to include an AD that would apply to all Airbus Model A310-
200 and -300 series airplanes. That NPRM was published in the Federal 
Register on February 13, 2006 (71 FR 7449). That NPRM proposed to 
require 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. That NPRM also proposed to require modifying the holes in 
the internal angle and tee fitting by cold expansion.

Comments

    We provided the public the opportunity to participate in the 
development of this AD. We received no comments on the NPRM or on the 
determination of the cost to the public.

Conclusion

    We have carefully reviewed the available data and determined that 
air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this AD. This AD will affect about 56 airplanes of U.S. 
registry. Work hours and parts costs vary according to the 
configuration of the airplane.

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                            Average
           Action             Work hour    labor rate        Parts         Cost per airplane      Fleet cost
                                            per hour
----------------------------------------------------------------------------------------------------------------
Inspection.................       16-306          $65       $618-$18,489  $1,658-$38,379,     $92,848-$2,149,224
                                                                           per inspection      , per inspection
                                                                           cycle.              cycle.
Modification...............      146-381           65       4,350-15,501  $13,840-$40,266...  $775,040-$2,254,89
                                                                                               6.
----------------------------------------------------------------------------------------------------------------

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 have 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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866;
    (2) Is not a ``significant rule'' under 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. See the ADDRESSES 
section for a location to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
Accordingly, under the authority delegated to me by the Administrator, 
the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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


Sec.  39.13  [Amended]

0
2. The Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

2006-09-05 Airbus: Amendment 39-14575. Docket No. FAA-2006-23870; 
Directorate Identifier 2005-NM-022-AD.

Effective Date

    (a) This AD becomes effective June 7, 2006.

Affected ADs

    (b) Certain requirements of this AD terminate certain 
requirements of AD 98-26-01, amendment 39-10942.

Applicability

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

Unsafe Condition

    (d) This AD results from full-scale fatigue tests, which 
revealed cracks in the lower rear spar internal angle and tee 
fitting. We are issuing this AD to detect and correct fatigue cracks 
of the rear spar internal angle and tee fitting, which could lead to 
the rupture of the internal angle, tee fitting, and rear spar, and 
consequent reduced structural integrity of the wings.

Compliance

    (e) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Initial and Repetitive Inspections

    (f) At the later of the times specified in paragraphs (f)(1) and 
(f)(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 06, dated July 13, 2004, except as 
required by paragraphs (k), (l), and (m) of this AD. Do all 
applicable related investigative and corrective actions before 
further flight.

[[Page 25923]]

    (1) Within 1,000 flight cycles or 1,600 flight hours after the 
effective date of this AD, whichever is first.
    (2) At the applicable time specified in Table 1 of this AD.

   Table 1.--Initial Compliance Times for the Rear Spar Internal Angle
------------------------------------------------------------------------
    Airplane model and configuration                Threshold
------------------------------------------------------------------------
Model A310-203, -204, -221, and -222     Before the accumulation of
 airplanes that are not modified by       10,300 total flight cycles or
 Airbus Modifications 06672S6812 and      16,600 total flight hours,
 07387S7974.                              whichever is first.
Model A310-203, -204, -221, and -222     Before the accumulation of
 airplanes that are modified by Airbus    23,400 total flight cycles or
 Modifications 06672S6812 and             37,700 total flight hours,
 07387S7974 (modified either in           whichever is first.
 production or in accordance with
 Airbus Service Bulletin A310-57-2035).
Model A310-304, -322, -324, and -325     Before the accumulation of
 airplanes that are not modified by       9,500 total flight cycles or
 Airbus Modifications 06672S6812 and      15,000 total flight hours,
 07387S7974.                              whichever is first.
Model A310-304, -322, -324, and -325     Before the accumulation of
 airplanes that are modified by Airbus    21,500 total flight cycles or
 Modifications 06672S6812 and             34,000 total flight hours,
 07387S7974 (modified either in           whichever is first.
 production or according to Airbus
 Service Bulletin A310-57-2035).
------------------------------------------------------------------------

    (g) Repeat the inspection specified in paragraph (f) of this AD 
thereafter at the applicable time specified in paragraph (g)(1) or 
(g)(2) of this AD.
    (1) For Model A310-203, -204, -221, and -222 airplanes: Repeat 
thereafter at intervals not to exceed 9,100 flight cycles or 14,650 
flight hours, whichever is first.
    (2) For Model A310-304, -322, -324, and -325 airplanes: Repeat 
thereafter at intervals not to exceed 9,500 flight cycles or 15,000 
flight hours, whichever is first.
    (h) At the applicable time specified in Table 2 of this AD or 
within 6 months after the effective date of this AD, whichever 
occurs later: 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 06, dated July 13, 2004, except as required by paragraphs 
(k), (l), and (m) of this AD. Do all applicable related 
investigative and corrective actions before further flight.

         Table 2.--Initial Compliance Times for the Tee Fitting
------------------------------------------------------------------------
    Airplane model and configuration                Threshold
------------------------------------------------------------------------
Model A310-203, -204, -221, and -222     Before the accumulation of
 airplanes that are not modified by       21,600 total flight cycles or
 Airbus Modification 06673S6813.          34,800 total flight hours,
                                          whichever is first.
Model A310-203, -204, -221, and -222     Before the accumulation of
 airplanes that are modified by Airbus    41,300 total flight cycles or
 Modification 06673S6813 (modified        66,500 total flight hours,
 either in production or in accordance    whichever is first.
 with Airbus Service Bulletin A310-57-
 2035).
Model A310-304, -322, -324, and -325     Before the accumulation of
 airplanes that are not modified by       17,100 total flight cycles or
 Airbus Modification 06673S6813.          27,000 total flight hours,
                                          whichever is first.
Model A310-304, -322, -324, and -325     Before the accumulation of
 airplanes that are modified by Airbus    32,300 total flight cycles or
 Modification 06673S6813 (modified        51,000 total flight hours,
 either in production or in accordance    whichever is first.
 with Airbus Service Bulletin A310-57-
 2035).
------------------------------------------------------------------------

    (i) Repeat the inspection specified in paragraph (h) of this AD 
thereafter at the applicable time specified in paragraph (i)(1) or 
(i)(2) of this AD.
    (1) For Model A310-203, -204, -221, and -222 airplanes: Repeat 
thereafter at intervals not to exceed 10,800 flight cycles or 17,400 
flight hours, whichever is first.
    (2) For Model A310-304, -322, -324, and -325 airplanes: Repeat 
thereafter at intervals not to exceed 8,800 flight cycles or 13,900 
flight hours, whichever is first.

Modification

    (j) For all airplanes except those that are modified by Airbus 
Modifications 06672S6812, 06673S6813, and 07387S7974 in production: 
Within 60 months after the effective date of this AD, 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, except as required by paragraph (k) of this AD. Do all 
applicable related investigative and corrective actions before 
further flight.

Contact the FAA

    (k) Where Airbus Service Bulletin A310-57-2035, Revision 08, 
dated September 19, 2005; and Airbus Service Bulletin A310-57-2047, 
Revision 06, dated July 13, 2004; specify 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).

Touch-and-Go Flights

    (l) All touch-and-go landings must be counted in determining the 
total number of flight cycles between consecutive inspections.

No Reporting Required

    (m) Although Airbus Service Bulletin A310-57-2047, Revision 06, 
dated July 13, 2004, specifies to submit certain information to the 
manufacturer, this AD does not include that requirement.

Actions Accomplished According to Previous Issues of Service Bulletins

    (n) Actions accomplished before the effective date of this AD in 
accordance with Airbus Service Bulletin A310-57-2047, Revision 03, 
dated November 26, 1997; Revision 04, dated March 5, 1999; or 
Revision 05, dated August 3, 2000; are considered acceptable for 
compliance with the corresponding actions specified in paragraphs 
(f) through (i) of this AD.
    (o) Actions accomplished before the effective date of this AD in 
accordance with Airbus Service Bulletin A310-57-2035, Revision 1, 
dated October 13, 1989; Revision 2, dated February 26, 1990; 
Revision 3, dated May 23, 1990; Revision 4, dated April 15, 1991; 
Revision 5, dated May 27, 1992; Revision 6, dated March 8, 1994; or 
Revision 7, dated April 17, 1996; are considered acceptable for 
compliance with the corresponding actions specified in paragraph (j) 
of this AD.

[[Page 25924]]

Related AD

    (p) Accomplishing the initial inspections specified in 
paragraphs (f) and (g) of this AD terminates the requirements 
specified in paragraph (o) of AD 98-26-01.

Alternative Methods of Compliance (AMOCs)

    (q)(1) The Manager, International Branch, ANM-116, has the 
authority to approve AMOCs for this AD, if requested in accordance 
with the procedures found in 14 CFR 39.19.
    (2) Before using any AMOC approved in accordance with 14 CFR 
39.19 on any airplane to which the AMOC applies, notify the 
appropriate principal inspector in the FAA Flight Standards 
Certificate Holding District Office.

Related Information

    (r) French airworthiness directive F-2005-001, dated January 5, 
2005, also addresses the subject of this AD.

Material Incorporated by Reference

    (s) You must use Airbus Service Bulletin A310-57-2047, Revision 
06, dated July 13, 2004; and Airbus Service Bulletin A310-57-2035, 
Revision 08, dated September 19, 2005; as applicable, to perform the 
actions that are required by this AD, unless the AD specifies 
otherwise. Airbus Service Bulletin A310-57-2047, Revision 06, dated 
July 13, 2004, includes the following effective pages:

----------------------------------------------------------------------------------------------------------------
                Page Nos.                   Revision level shown on page             Date shown on page
----------------------------------------------------------------------------------------------------------------
1-8, 10-15, 17, 18, 22-25, 33, 37.......  06.............................  July 13, 2004.
9, 16, 21, 30, 45, 46, 75-80, 95, 96....  05.............................  August 3, 2000.
19, 20, 27-29, 35, 36, 47-56, 61-74.....  Original.......................  February 26, 1991.
26, 31, 32, 34, 39-44, 59, 60, 81-94....  04.............................  March 5, 1999.
38......................................  1..............................  January 4, 1996.
57, 58..................................  2..............................  January 22, 1997.
----------------------------------------------------------------------------------------------------------------

    The Director of the Federal Register approved the incorporation 
by reference of these documents in accordance with 5 U.S.C. 552(a) 
and 1 CFR part 51. Contact Airbus, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France, for a copy of this service information. 
You may review copies at the Docket Management Facility, U.S. 
Department of Transportation, 400 Seventh Street, SW., Room PL-401, 
Nassif Building, Washington, DC; on the Internet at <a href="http://dms.dot.gov">http://dms.dot.gov</a>; or at the National Archives and Records Administration 
(NARA). For information on the availability of this material at the 
NARA, call (202) 741-6030, or go to <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

    Issued in Renton, Washington, on April 20, 2006.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 06-4052 Filed 5-2-06; 8:45 am]
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