[Federal Register: February 26, 2009 (Volume 74, Number 37)]
[Rules and Regulations]
[Page 8728-8732]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr26fe09-11]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0908; Directorate Identifier 2007-NM-190-AD;
Amendment 39-15788; AD 2009-01-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
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SUMMARY: The FAA is superseding an existing airworthiness directive
(AD) that applies to all Airbus Model A310 series airplanes. That AD
currently requires repetitive detailed inspections to detect cracks
propagating from the fastener holes that attach the left- and right-
hand pick-up angles at frame 40 to the wing lower skin and fuselage
panel, and corrective actions if necessary. This new AD revises the
intervals for accomplishing the repetitive detailed inspections and
provides for an optional terminating modification for the repetitive
inspections. This new AD also revises the applicability of the AD to
remove certain airplanes. This AD results from mandatory continuing
airworthiness information originated by an aviation authority of
another country to identify and correct an unsafe condition on an
aviation product. We are issuing this AD to prevent reduced structural
integrity of the airplane due to fatigue damage, and consequent
cracking of the pick-up angles at frame 40.
DATES: This AD is effective April 2, 2009.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 2,
2009.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
February 9, 2001 (66 FR 1031, January 5, 2001).
ADDRESSES: For service information identified in this 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.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The address for the
Docket Office (telephone 800-647-5527) is the Document Management
Facility, U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer,
International Branch, ANM-116,
[[Page 8729]]
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-2125; fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an airworthiness directive (AD) that supersedes AD
2000-26-14, amendment 39-12064 (66 FR 1031, January 5, 2001). The
existing AD applies to all Airbus Model A310 series airplanes. That
NPRM was published in the Federal Register on August 26, 2008 (73 FR
50250). A correction to that NPRM was published in the Federal Register
on September 8, 2008 (73 FR 51961). That NPRM proposed to continue to
require repetitive detailed inspections to detect cracks propagating
from the fastener holes that attach the left- and right-hand pick-up
angles at frame 40 to the wing lower skin and fuselage panel, and
corrective actions if necessary. That NPRM also proposed to revise the
intervals for accomplishing the repetitive detailed inspections and
provided for an optional terminating modification for the repetitive
inspections. That NPRM also proposed to revise the applicability of the
AD to remove certain airplanes.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the relevant data and determined that air safety and
the public interest require adopting the AD as proposed.
Costs of Compliance
This AD affects about 68 Model A310 series airplanes of U.S.
registry.
The inspections that are required by AD 2000-26-14 and retained in
this AD take about 2 work hours per airplane, at an average labor rate
of $80 per work hour. Based on these figures, the estimated cost of the
currently required actions is $10,880, or $160 per airplane, per
inspection cycle.
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
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.
You can find our regulatory evaluation and the estimated costs of
compliance in the AD Docket.
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 FAA amends Sec. 39.13 by removing amendment 39-12064 (66 FR
1031, January 5, 2001) and by adding the following new AD:
2009-01-09 Airbus: Amendment 39-15788. Docket No. FAA-2008-0908;
Directorate Identifier 2007-NM-190-AD.
Effective Date
(a) This airworthiness directive (AD) is effective April 2,
2009.
Affected ADs
(b) This AD supersedes AD 2000-26-14.
Applicability
(c) This AD applies to Airbus Model A310 series airplanes,
certificated in any category, except those airplanes modified in-
service in accordance with Airbus Service Bulletin A310-53-2119,
dated October 25, 2005; or Revision 01, dated February 27, 2007.
Unsafe Condition
(d) This AD results from mandatory continuing airworthiness
information originated by an aviation authority of another country
to identify and correct an unsafe condition on an aviation product.
We are issuing this AD to prevent reduced structural integrity of
the airplane due to fatigue damage and consequent cracking of the
pick-up angles at frame 40.
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.
Requirements of AD 2000-26-14
Inspections and Corrective Actions
(f) Perform a detailed inspection to detect cracks propagating
from the fastener holes that attach the left- and right-hand pick-up
angles at frame 40 to the wing lower skin and fuselage panel, at the
time specified in paragraph (g), (h), (i), (j), or (k) of this AD,
as applicable. Perform the actions in accordance with Figure 2,
Sheet 1, ``Synoptic Chart,'' of Airbus Service Bulletin A310-
53A2111, Revision 01, dated June 21, 2000, except as provided by
paragraph (l) of this AD.
(1) If no cracking is found during the inspection required by
paragraph (f) of this AD, repeat the detailed inspection thereafter
at the interval specified in paragraph (f)(1)(i) or (f)(1)(ii) of
this AD, as applicable, except as provided by paragraph (n) of this
AD.
(i) For Model A310-200 series airplanes: Except as provided by
paragraph (i) of this AD, repeat the inspection thereafter at
intervals not to exceed 1,000 flight cycles or 2,600 flight hours,
whichever occurs first.
(ii) For Model A310-300 series airplanes: Except as provided by
paragraphs (i) of this AD, repeat the inspection thereafter at
intervals not to exceed 850 flight cycles or 2,800 flight hours,
whichever occurs first.
(2) If any cracking is found during the inspection required by
paragraph (f) of this AD, prior to further flight, perform
applicable corrective actions (including repair (drilling and
reaming a crack stop hole in the pick-up angle, performing a
Rototest inspection and repetitive detailed inspections at the time
specified in the service bulletin, and replacing the pick-up angle
with a new angle at the time specified in the service bulletin,
[[Page 8730]]
except as provided by paragraph (o) of this AD); or immediate
replacement of any cracked angle with a new angle). Perform the
actions and repetitive inspections in accordance with Figure 2,
Sheet 1, ``Synoptic Chart,'' of Airbus Service Bulletin A310-
53A2111, Revision 01, dated June 21, 2000, except as provided by
paragraph (l) of this AD.
Note 1: Accomplishment of the actions required by paragraph (f)
of this AD in accordance with Airbus Service Bulletin A310-53A2111,
dated April 21, 2000, is considered to be acceptable for compliance
with the requirements of that paragraph.
Compliance Times
(g) For Model A310-200 series airplanes: Except as provided by
paragraphs (i), (j), and (k) of this AD, perform the initial
inspection at the later of the times specified in paragraphs (g)(1)
and (g)(2) of this AD.
(1) Prior to the accumulation of 7,900 total flight cycles or
23,600 total flight hours, whichever occurs first.
(2) Within 700 flight cycles or 1,200 flight hours after
February 9, 2001 (the effective date of AD 2000-26-14), whichever
occurs first.
(h) For Model A310-300 series airplanes: Except as provided by
paragraphs (i), (j), and (k) of this AD, perform the initial
inspection required by paragraph (f) of this AD at the later of the
times specified in paragraphs (h)(1) and (h)(2) of this AD.
(1) Prior to the accumulation of 6,700 total flight cycles or
24,700 total flight hours, whichever occurs first.
(2) Within 700 flight cycles or 1,200 flight hours after
February 9, 2001, whichever occurs first.
(i) For airplanes that have accumulated more than 18,000 total
flight cycles or 53,000 total flight hours as of February 9, 2001:
Perform the initial inspection required by paragraph (f) of this AD
within 350 flight cycles or 600 flight hours after February 9, 2001,
whichever occurs first. Repeat the inspection thereafter at
intervals not to exceed 350 flight cycles or 600 flight hours,
whichever occurs first.
(j) For airplanes having manufacturer's serial number 0162
through 0326 inclusive, on which Airbus Service Bulletin A310-53-
2014 has been accomplished prior to February 9, 2001: The initial
inspection threshold may be counted from the date of accomplishment
of Airbus Service Bulletin A310-53-2014.
(k) For airplanes on which a pick-up angle has been replaced:
For that pick-up angle only, the initial inspection threshold may be
counted from the date of installation of the new pick-up angle.
Note 2: For the purposes of this AD, a detailed inspection is
defined as: ``An intensive visual examination of a specific
structural area, system, installation, or assembly to detect damage,
failure, or irregularity. Available lighting is normally
supplemented with a direct source of good lighting at intensity
deemed appropriate by the inspector. Inspection aids such as mirror,
magnifying lenses, etc., may be used. Surface cleaning and elaborate
access procedures may be required.''
New Requirements of This AD
New Revisions of Service Bulletin
(l) As of the effective date of this AD, use only the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A310-53-2111, Revision 03, dated May 21, 2007, to do the inspections
and corrective actions required by paragraph (f) of this AD; except
where Figure 2 Sheet 2 of Airbus Mandatory Service Bulletin A310-53-
2111, Revision 03, dated May 21, 2007, specifies actions for crack
length of ``<54 mm (2.126 in.)'' and ``<69 mm (2.716 in.),'' this AD
requires the corresponding actions for crack lengths less than or
equal to those measurements.
(m) Inspections and applicable corrective actions done before
the effective date of this AD in accordance with Airbus Mandatory
Service Bulletin A310-53-2111, Revision 02, dated October 25, 2005,
are acceptable for compliance with the requirements of paragraph (f)
of this AD.
Revised Repetitive Intervals for Detailed Inspections
(n) As of the effective date of this AD, repeat the detailed
inspections for no crack findings required by paragraph (f)(1)(i),
(f)(1)(ii), or (i) of this AD, as applicable, at the applicable
times specified in Table 1 of this AD, until the modification
specified in paragraph (p) of this AD is done.
Table 1--Revised Repetitive Intervals for Certain Detailed Inspections
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For model-- Repeat the inspection at the later of the And thereafter at
following times-- intervals not to
exceed--
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(1) A310-200 series airplanes........ Within 950 flight Within 50 flight cycles 950 flight cycles or
cycles or 1,900 flight or 250 flight hours 1,900 flight hours,
hours since the last after the effective whichever occurs
inspection required by date of this AD, first.
paragraph (f)(1)(i) or whichever occurs first.
(i) of this AD,
whichever occurs first.
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(2) A310-300 series airplanes (short Within 900 flight Within 50 flight cycles 900 flight cycles or
range). cycles or 2,550 flight or 250 flight hours 2,550 flight hours,
hours since the last after the effective whichever occurs
inspection required by date of this AD, first.
paragraph (f)(1)(ii) whichever occurs first.
or (i) of this AD,
whichever occurs first.
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(3) A310-300 series airplanes (long Within 800 flight Within 50 flight cycles 800 flight cycles or
range). cycles or 4,000 flight or 250 flight hours 4,000 flight hours,
hours since the last after the effective whichever occurs
inspection required by date of this AD, first.
paragraph (f)(1)(ii) whichever occurs first.
or (i) of this AD,
whichever occurs first.
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Revised Threshold for Replacing the Pick-Up Angles
(o) As of the effective date of this AD, do the replacement of
the pick-up angle required by paragraph (f)(2) of this AD, at the
applicable time specified in Table 2 of this AD.
[[Page 8731]]
Table 2--Revised Thresholds for Replacing Pick-Up Angles
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For model-- Replace at the earlier of the
following times--
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(1) A310-200 series airplanes... At the time Within 1,500
specified in flight cycles or
paragraph (f)(2) 3,000 flight
of this AD for hours since the
replacing the last detailed
pick-up angle. inspection, or
within 30 days
after the
effective date of
this AD,
whichever occurs
later.
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(2) A310-300 series airplanes At the time Within 1,600
(short range). specified in flight cycles or
paragraph (f)(2) 4,600 flight
of this AD for hours since the
replacing the last detailed
pick-up angle. inspection, or
within 30 days
after the
effective date of
this AD,
whichever occurs
later.
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(3) A310-300 series airplanes At the time Within 1,400
(long range). specified in flight cycles or
paragraph (f)(2) 7,200 flight
of this AD for hours since the
replacing the last detailed
pick-up angle. inspection, or
within 30 days
after the
effective date of
this AD,
whichever occurs
later.
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Optional Terminating Modification
(p) Remove the existing pick-up angles and install a reinforced
doubler between frames (FR) FR40 and FR41, and perform applicable
related investigative and corrective actions by accomplishing all
the applicable actions specified in the Accomplishment Instructions
of Airbus Service Bulletin A310-53-2119, Revision 01, dated February
27, 2007; except as provided by paragraph (q) of this AD.
Accomplishing these actions ends the repetitive inspections required
by this AD.
(q) If any crack is detected and Airbus Service Bulletin A310-
53-2119, Revision 01, dated February 27, 2007, specifies to contact
Airbus: Before further flight, repair the crack using a method
approved by either the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the European Aviation Safety
Agency (EASA) (or its delegated agent).
(r) Actions done before the effective date of this AD in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A310-53-2119, dated October 25, 2005, are acceptable for
compliance with the corresponding requirements of paragraph (p) of
this AD.
Alternative Methods of Compliance (AMOCs)
(s) The Manager, International Branch, ANM-116, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send information to ATTN: Dan
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. Before
using any approved AMOC on any airplane to which the AMOC applies,
notify your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO.
Related Information
(t) EASA airworthiness directive 2007-0184, dated July 3, 2007,
also addresses the subject of this AD.
Material Incorporated by Reference
(u) You must use the service information identified in Table 3
of this AD to do the actions required by this AD, unless the AD
specifies otherwise. If you do the optional terminating modification
provided in this AD, you must use Airbus Service Bulletin A310-53-
2119, Revision 01, including Appendix 01, dated February 27, 2007,
to do the optional terminating modification.
Table 3--Material Incorporated by Reference for Actions required by This
AD
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Revision
Service bulletin level Date
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Airbus Service Bulletin A310- 01 June 21, 2000.
53A2111, including Appendix
01.
Airbus Mandatory Service 03 May 21, 2007.
Bulletin A310-53-2111,
including Appendix 01.
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(1) The Director of the Federal Register approved the
incorporation by reference of the service information identified in
Table 4 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.
Table 4--New Material Incorporated by Reference
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Revision
Service bulletin level Date
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Airbus Mandatory Service 03 May 21, 2007.
Bulletin A310-53-2111,
including Appendix 01.
A310-53-2119, including 01 February 27, 2007.
Appendix 01.
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(2) The Director of the Federal Register previously approved the
incorporation by reference of Airbus Service Bulletin A310-53A2111,
Revision 01, including Appendix 1, dated June 21, 2000, on February
9, 2001 (66 FR 1031, January 5, 2001).
(3) For service information identified in this 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.
(4) You may review copies of the service information that is
incorporated by reference 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 or 425-227-1152.
(5) You may also review copies of the service information at the
National Archives and Records Administration (NARA). For information
on the availability of this material at NARA, call 202-741-6030, or
go to: http://www.archives.gov/federal_register/
[[Page 8732]]
code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on December 18, 2008.
Stephen P. Boyd,
Assistant Manager, Transport Airplane Directorate, Aircraft
Certification Service.
[FR Doc. E9-3765 Filed 2-25-09; 8:45 am]
BILLING CODE 4910-13-P