[Federal Register: February 13, 2006 (Volume 71, Number 29)]
[Proposed Rules]
[Page 7449-7452]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr13fe06-15]
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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).
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(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
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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 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).
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(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]
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