[Federal Register Volume 71, Number 29 (Monday, February 13, 2006)]
[Proposed Rules]
[Pages 7449-7452]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E6-1942]


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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]
RIN 2120-AA64


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

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

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: The FAA proposes to adopt a new airworthiness directive (AD) 
for all Airbus Model A310-200 and -300 series airplanes. This proposed 
AD would 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. This proposed AD would also require modifying the holes in 
the internal angle and tee fitting by cold expansion. This proposed AD 
results from full-scale fatigue tests, which revealed cracks in the 
lower rear spar internal angle, and tee fitting. We are proposing 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: We must receive comments on this proposed AD by March 15, 2006.

ADDRESSES: Use one of the following addresses to submit comments on 
this proposed AD.
     DOT Docket Web site: Go to http://dms.dot.gov and follow 
the instructions for sending your comments electronically.
     Government-wide rulemaking Web site: Go to http://www.regulations.gov and follow the instructions for sending your 
comments electronically.
     Mail: Docket Management Facility, U.S. Department of 
Transportation, 400 Seventh Street, SW., Nassif Building, room PL-401, 
Washington, DC 20590.
     Fax: (202) 493-2251.
     Hand Delivery: Room PL-401 on the plaza level of the 
Nassif Building, 400 Seventh Street, SW., Washington, DC, between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    Contact Airbus, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, 
France, for service information identified in this proposed AD.

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

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to submit any relevant written data, views, or 
arguments regarding this proposed AD. Send your comments to an address 
listed in the ADDRESSES section. Include the docket number ``FAA-2006-
23870; Directorate Identifier 2005-NM-022-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of the proposed AD. We will 
consider all comments received by the closing date and may amend the 
proposed AD in light of those comments.
    We will post all comments we receive, without change, to http://dms.dot.gov, including any personal information you provide. We will 
also post a report summarizing each substantive verbal contact with FAA 
personnel concerning this proposed AD. Using the search function of 
that web site, anyone can find and read the

[[Page 7450]]

comments in any of our dockets, including the name of the individual 
who sent the comment (or signed the comment on behalf of an 
association, business, labor union, etc.). You may review the DOT's 
complete Privacy Act Statement in the Federal Register published on 
April 11, 2000 (65 FR 19477-78), or you may visit http://dms.dot.gov.

Examining the Docket

    You may examine the AD docket on the Internet at http://dms.dot.gov, 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 DOT 
street address stated in the ADDRESSES section. Comments will be 
available in the AD docket shortly after the Docket Management System 
receives them.

Discussion

    The Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC), 
which is the airworthiness authority for France, notified us that an 
unsafe condition may exist on all Airbus Model A310-200 and -300 series 
airplanes. During full-scale fatigue tests of the A310 airplane, the 
manufacturer found cracks at approximately 70,000 total flight cycles 
in the tee fitting at stiffener 8 on both sides of the center wing box, 
in the lower rear spar, and in the internal angles on both sides of the 
center wing box. DGAC advises that analysis of in-service inspections 
results has led the manufacturer to modify the existing inspection 
program, which is specified in action 1.14 of French airworthiness 
directive 1992-106-132(B) R6, dated June 25, 2003. The DGAC recommends 
that the thresholds and intervals be decreased and that a modification 
of the rear spar internal angle and tee fitting is needed to address 
fatigue cracks. Fatigue cracks of the rear spar internal angle and tee 
fitting, if not corrected, could lead to the rupture of the internal 
angle, tee fitting, and rear spar, and consequent reduced structural 
integrity of the wings.

Other Relevant Rulemaking

    On December 8, 1998, we issued AD 98-26-01, amendment 39-10942 (63 
FR 69179, December 16, 1998), for all Airbus Model A310 series 
airplanes, to require various inspections to detect fatigue cracks at 
certain locations on the fuselage, horizontal stabilizer, and wings and 
tail, and repair or modification, if necessary; and installation of 
doublers. Paragraph (o) of AD 98-26-01, for certain airplanes, requires 
repetitive rotating probe inspections to detect cracks in the fastener 
holes on the left- and right-hand sides of the rear spar internal angle 
and tee fitting, in accordance with Airbus Service Bulletin A310-57-
2047, Revision 2, dated January 22, 1997. Certain actions in this 
proposed AD would terminate the requirements of paragraph (o) of AD 98-
26-01.

Relevant Service Information

    Airbus has issued Service Bulletin A310-57-2047, Revision 06, dated 
July 13, 2004. The service bulletin describes procedures for performing 
repetitive rotating probe inspections for any crack of the rear spar 
internal angle and the left and right sides of the tee fitting located 
in the center wing box, and doing related investigative and corrective 
actions if necessary. The corrective actions include oversizing holes, 
replacing bolts with new bolts, and contacting the manufacturer if any 
crack is beyond certain limits. The related investigative action is 
doing a rotating probe inspection for any crack after a hole has been 
oversized.
    Airbus has also issued Service Bulletin A310-57-2035, Revision 08, 
dated September 19, 2005. The service bulletin describes procedures for 
modifying the holes in the internal angle and tee fitting by cold 
expansion (including doing related investigative and corrective 
actions). The related investigative and corrective actions include 
performing a rotating probe inspection for any crack of the bolt holes 
of the internal angle and tee fitting and contacting the manufacturer 
if any crack is found.
    Accomplishing the actions specified in the service information is 
intended to adequately address the unsafe condition. The DGAC mandated 
the service information and issued French airworthiness directive F-
2005-001, dated January 5, 2005, to ensure the continued airworthiness 
of these airplanes in France.

FAA's Determination and Requirements of the Proposed AD

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
section 21.29 of the Federal Aviation Regulations (14 CFR 21.29) and 
the applicable bilateral airworthiness agreement. Pursuant to this 
bilateral airworthiness agreement, the DGAC has kept the FAA informed 
of the situation described above. We have examined the DGAC's findings, 
evaluated all pertinent information, and determined that we need to 
issue an AD for airplanes of this type design that are certificated for 
operation in the United States.
    Therefore, we are proposing this AD, which would require 
accomplishing the actions specified in the service information 
described previously, except as discussed under ``Differences Between 
the Proposed AD and the Service Bulletins.''

Differences Between the Proposed AD and the Service Bulletins

    The service bulletins specify to contact the manufacturer if 
certain cracks are found, but this proposed AD would require repairing 
those conditions using a method that we or the DGAC (or its delegated 
agent) approve. In light of the type of repair that would be required 
to address the unsafe condition, and consistent with existing bilateral 
airworthiness agreements, we have determined that, for this proposed 
AD, a repair we or the DGAC approve would be acceptable for compliance 
with this proposed AD.
    Operators should also note that, unlike particular provisions in 
Airbus Service Bulletin A310-57-2047, Revision 06, dated July 13, 2004, 
regarding adjustment of the compliance times using an ``inspection 
threshold formula, this proposed AD would not permit formulaic 
adjustments of the inspection compliance times. We have determined that 
such adjustments may present difficulties in determining if the initial 
inspection following installation of the modification in accordance 
with the service bulletin has been accomplished within the appropriate 
time frame. Further, while such adjustable compliance times are 
utilized as part of the Maintenance Review Board program, they do not 
fit practically into the AD tracking process for operators or for 
Principal Maintenance Inspectors attempting to ascertain compliance 
with ADs. Based on reviews of the ``inspection threshold'' calculations 
with the Aircraft Evaluation Group, and in further consultation with 
the manufacturer, we have determined that fixed compliance times should 
be specified for accomplishment of the actions specified in this 
proposed AD. However, operators may request an extension of the 
compliance times of this AD in accordance with the ``inspection 
threshold'' formula, under the provisions of paragraph (q) of this AD.

Costs of Compliance

    The following table provides the estimated costs for U.S. operators 
to comply with this proposed AD. This

[[Page 7451]]

proposed AD would affect about 56 airplanes of U.S. registry. Work 
hours and parts costs vary according to the configuration of the 
airplane.

                                                                     Estimated Costs
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                                                          Average labor
                 Action                    Work hours     rate per hour           Parts                Cost per airplane              Fleet cost
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Inspection.............................          16-306             $65             $618-$18,489  $1,658-$38,379, per         $92,848-$2,149,224, per
                                                                                                   inspection cycle.           inspection cycle.
Modification...........................         146-381             $65           $4,350-$15,501  $13,840-$40,266...........  $775,040-$2,254,896.
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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 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 that the 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. 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, 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 Federal Aviation Administration (FAA) amends Sec.  39.13 by 
adding the following new airworthiness directive (AD):

Airbus: Docket No. FAA-2006-23870; Directorate Identifier 2005-NM-
022-AD.

Comments Due Date

    (a) The FAA must receive comments on this AD action by March 15, 
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.
    (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
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    Airplane model and configuration                Threshold
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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.

[[Page 7452]]

 
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.

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.

    Issued in Renton, Washington, on February 1, 2006.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. E6-1942 Filed 2-10-06; 8:45 am]
BILLING CODE 4910-13-P