[Federal Register: June 17, 2008 (Volume 73, Number 117)]
[Proposed Rules]
[Page 34224-34228]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17jn08-12]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0657; Directorate Identifier 2007-NM-296-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300, A310, and A300-600
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 supersede an existing airworthiness
directive (AD) that applies to certain Airbus Model A300, A310, and
A300-600 series airplanes. The existing AD currently requires
repetitive detailed visual inspections to detect cracks in the pylon
thrust and sideload fitting of the wing, and replacement of any cracked
pylon thrust and sideload fitting with a new fitting. This proposed AD
would
[[Page 34225]]
reduce the threshold and repetitive intervals for the detailed
inspection for certain airplanes and would reduce the applicability of
the existing AD. This proposed AD results from issuance of mandatory
continuing airworthiness information by a foreign civil airworthiness
authority. We are proposing this AD to detect and correct cracks in the
pylon thrust and sideload fitting of the wing, which could result in
reduced structural integrity of the airplane.
DATES: We must receive comments on this proposed AD by July 17, 2008.
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 W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590, between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays.
For service information identified in this AD, contact Airbus, 1
Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France.
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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket 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: Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425)
227-1138; 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-2008-0657;
Directorate Identifier 2007-NM-296-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 because of those comments.
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 July 24, 1998, we issued AD 98-16-11, amendment 39-10687 (63 FR
40816, July 31, 1998), for certain Airbus Model A300, A310, and A300-
600 series airplanes. That AD requires repetitive detailed visual
inspections to detect cracks in the pylon thrust and sideload fitting
of the wing, and replacement of any cracked pylon thrust and sideload
fitting with a new fitting. That AD resulted from issuance of mandatory
continuing airworthiness information by a foreign civil airworthiness
authority. We issued that AD to detect and correct cracks in the pylon
thrust and sideload fitting of the wing, which could result in reduced
structural integrity of the airplane.
Actions Since Existing AD Was Issued
Since we issued AD 98-16-11, Airbus has issued the following
service bulletins:
Table.--New Service Bulletins
------------------------------------------------------------------------
Airbus service bulletin-- For model--
------------------------------------------------------------------------
A300-57-0232, Revision 02, A300 series airplanes.
dated February 21, 2000.
A300-57-6079, Revision 04, A300-600 series airplanes.
dated February 21, 2000.
A310-57-2075, Revision 03, A310 series airplanes.
dated December 1, 2006.
------------------------------------------------------------------------
The repetitive detailed inspections and replacement procedures are
essentially identical to those specified in previous issues of the
service bulletins. (AD 98-16-11 refers to Airbus Service Bulletins
A300-57-0232, Revision 01 (for Model A300 series airplanes); A310-57-
2075, Revision 01 (for Model A310 series airplanes); and A300-57-6079,
Revision 02 (for Model A300-600 series airplanes); all dated January
12, 1998; as the appropriate sources of service information for
accomplishing the required actions.) Revision 03 of Airbus Service
Bulletin A310-57-2075 reduces the detailed inspection thresholds and
repeat intervals for certain airplanes. In addition, the effectivity
listing of all three service bulletins has been revised to remove
airplanes that have been scrapped. No more work is necessary for
airplanes on which previous issues of the service bulletins were done.
Accomplishing the actions specified in the service information is
intended to adequately address the unsafe condition. The European
Aviation Safety Agency (EASA), which is the Technical Agent for the
Member States of the European Community, mandated the service
information and issued EASA airworthiness directive 2007-0243, dated
September 4, 2007, to ensure the continued airworthiness of these
airplanes in the European Union.
FAA's Determination and Requirements of the Proposed AD
These airplanes 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. As described in FAA
Order 8100.14A, ``Interim Procedures for Working with the European
Community on Airworthiness Certification and Continued Airworthiness,''
dated August 12, 2005, the EASA has kept the FAA informed of the
situation described above. We have examined the EASA's findings,
evaluated all pertinent information, and determined that AD action is
necessary for airplanes of this type design that are certificated for
operation in the United States.
This proposed AD would supersede AD 98-16-11 and would continue to
require, at reduced thresholds and repetitive intervals for certain
airplanes, repetitive detailed visual inspections to detect cracks in
the pylon thrust and
[[Page 34226]]
sideload fitting of the wing, and would continue to require replacement
of any cracked pylon thrust and sideload fitting with a new fitting.
This proposed AD would also require accomplishing the actions specified
in service information described previously.
Differences Between Proposed Rule and EASA AD
The proposed AD would differ from the parallel EASA airworthiness
directive in that it would not allow for adjustment in compliance time
based on airplane utilization. In developing an appropriate compliance
time for this proposed AD, the FAA considered not only the
manufacturer's recommendation, but the degree of urgency associated
with addressing the subject unsafe condition, and the average
utilization of the affected fleet. In light of these factors, we find
the compliance times specified in paragraphs (f)(1) and (f)(2) of this
proposed AD to be warranted, in that they represent an appropriate
interval of time allowable for affected airplanes to continue to
operate without compromising safety.
Change to Existing AD
This proposed AD would retain all requirements of AD 98-16-11.
Since AD 98-16-11 was issued, the AD format has been revised, and
certain paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this proposed AD, as listed in
the following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement
Requirement in AD 98-16-11 in this proposed AD
------------------------------------------------------------------------
paragraph (a)............................. paragraph (f).
paragraph (b)............................. paragraph (g).
------------------------------------------------------------------------
In addition, we have revised the applicability of this proposed AD
to refer to the latest revisions of the service information described
previously.
We also changed all references to a ``detailed visual inspection''
in the existing AD to ``detailed inspection'' in this action.
Costs of Compliance
This proposed AD would affect about 164 Model A300, A310, and A300-
600 series airplanes of U.S. registry.
The inspections that are required by AD 98-16-11 and retained in
this proposed AD take about 3 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 $39,360, or $240 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
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
removing amendment 39-10687 (63 FR 40816, July 31, 1998) and adding the
following new airworthiness directive (AD):
Airbus: Docket No. FAA-2008-0657; Directorate Identifier 2007-NM-
296-AD.
Comments Due Date
(a) The FAA must receive comments on this AD action by July 17,
2008.
Affected ADs
(b) This AD supersedes AD 98-16-11.
Applicability
(c) This AD applies to Airbus airplanes identified in Table 1 of
this AD, certificated in any category.
Table 1.--Applicability
------------------------------------------------------------------------
As identified in Airbus service
Model-- bulletin--
------------------------------------------------------------------------
(1) A300 series airplanes............ A300-57-0232, Revision 02, dated
February 21, 2000.
(2) A310 series airplanes............ A310-57-2075, Revision 03, dated
December 1, 2006.
(3) A300-600 series airplanes........ A300-57-6079, Revision 04, dated
February 21, 2000.
------------------------------------------------------------------------
Unsafe Condition
(d) This AD results from issuance of mandatory continuing
airworthiness information by a foreign civil airworthiness
authority. We are issuing this AD to detect and correct cracks in
the pylon thrust and sideload fitting of the wing, which could
result in reduced structural integrity of the airplane.
Compliance
(e) You are responsible for having the actions required by this
AD performed within
[[Page 34227]]
the compliance times specified, unless the actions have already been
done.
Requirements of AD 98-16-11:
Repetitive Detailed Inspections at Reduced Thresholds and Repeat
Intervals for Certain Airplanes
(f) At the applicable time specified in paragraph (f)(1) or
(f)(2) of this AD: Perform a detailed inspection to detect cracks in
the pylon thrust and sideload fitting of the wing, in accordance
with Airbus Service Bulletin A300-57-0232, Revision 01 (for Model
A300 series airplanes); A310-57-2075, Revision 01 (for Model A310
series airplanes); or A300-57-6079, Revision 02 (for Model A300-600
series airplanes); all dated January 12, 1998; as applicable; except
as provided by paragraph (h) of this AD.
(1) For Model A300 and A300-600 series airplanes: Inspect prior
to the accumulation of 2,800 total flight cycles, or within 18
months after September 4, 1998 (the effective date AD 98-16-11),
whichever occurs later, and thereafter at intervals not to exceed
2,800 flight cycles.
(2) For Model A310 series airplanes: Inspect at the earlier of
the times specified in paragraph (f)(2)(i) and (f)(2)(ii) of this
AD. Repeat thereafter at the applicable intervals specified in Table
3 of this AD.
(i) Prior to the accumulation of 2,800 total flight cycles, or
within 18 months after September 4, 1998, whichever occurs later.
(ii) At the applicable time specified in Table 2 of this AD.
Table 2.--Reduced Inspection Thresholds for Model A310 Series Airplanes
------------------------------------------------------------------------
Compliance time (whichever occurs later)
Model -------------------------------------------
Threshold Grace period
------------------------------------------------------------------------
A310-200 series airplanes... Before the Within 800 flight
accumulation of cycles or 1,600
1,500 total flight flight hours after
cycles or 3,000 the effective date
total flight hours of this AD,
since first flight, whichever occurs
whichever occurs first.
first.
A310-300 series airplanes Before the Within 800 flight
(short range). accumulation of cycles or 1,600
1,300 total flight flight hours after
cycles or 3,800 the effective date
total flight hours of this AD,
since first flight, whichever occurs
whichever occurs first.
first.
A310-300 series airplanes Before the Within 800 flight
(long range). accumulation of 800 cycles or 1,600
total flight cycles flight hours after
or 4,000 total the effective date
flight hours since of this AD,
first flight, whichever occurs
whichever occurs first.
first.
------------------------------------------------------------------------
Table 3.--Reduced Repeat Intervals for Model A310 Series Airplanes
------------------------------------------------------------------------
Repeat the detailed And, thereafter
For Model-- inspection at the at intervals not
later of-- to exceed--
------------------------------------------------------------------------
A310-200 series airplanes..... Within 1,500 flight 1,500 flight
cycles or 3,000 cycles or 3,000
flight hours since flight hours,
the last detailed whichever
inspection, whichever occurs first.
occurs first; or
within 800 flight
cycles or 1,600
flight hours after
the effective date of
this AD, whichever
occurs first.
A310-300 series airplanes Within 1,300 flight 1,300 flight
(short range). cycles or 3,800 cycles or 3,800
flight hours since flight hours,
the last detailed whichever
inspection, whichever occurs first.
occurs first; or
within 800 flight
cycles or 1,600
flight hours after
the effective date of
this AD, whichever
occurs first.
A310-300 series airplanes Within 800 flight 800 flight
(long range). cycles or 4,000 cycles or 4,000
flight hours since flight hours,
the last detailed whichever
inspection, whichever occurs first.
occurs first; or
within 800 flight
cycles or 1,600
flight hours after
the effective date of
this AD, whichever
occurs first.
------------------------------------------------------------------------
Corrective Action
(g) If any crack is detected during any inspection required by
paragraph (f) of this AD, prior to further flight, replace the pylon
thrust and sideload fitting with a new fitting in accordance with
Airbus Service Bulletin A300-57-0232, Revision 01 (for Model A300
series airplanes); A310-57-2075, Revision 01 (for Model A310 series
airplanes); or A300-57-6079, Revision 02 (for Model A300-600 series
airplanes); all dated January 12, 1998; as applicable; except as
provided by paragraph (h) of this AD.
New Actions Required by This AD:
New Service Information
(h) For all airplanes: As of the effective date of this AD, use
only the Accomplishment Instructions of the applicable service
bulletin specified in Table 4 of this AD to do the repetitive
detailed inspections required by paragraph (f) of this AD and the
replacement required by paragraph (g) of this AD.
Table 4.--New Service Bulletins
------------------------------------------------------------------------
Airbus service bulletin-- For model--
------------------------------------------------------------------------
(1) A300-57-0232, Revision A300 series airplanes.
02, dated February 21, 2000.
(2) A300-57-6079, Revision A300-600 series airplanes.
04, dated February 21, 2000.
(3) A310-57-2075, Revision A310 series airplanes.
03, dated December 1, 2006.
------------------------------------------------------------------------
(i) Actions done before the effective date of this AD in
accordance with Airbus Service Bulletins A300-57-6079, Revision 02,
dated January 12, 1998, or Revision 03, dated October 25, 1999 (for
Model A300-600 series airplanes); A310-57-2075, Revision 01, dated
January 12, 1998, or Revision 02, dated February 21, 2000 (for Model
A310 series airplanes); or A300-57-0232, Revision 01, dated January
12, 1998 (for Model A300 series airplanes); are acceptable for
compliance with the corresponding requirements of this AD.
[[Page 34228]]
Alternative Methods of Compliance (AMOCs)
(j) 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: Vladimir
Ulyanov, Aerospace Engineer, International Branch, ANM-116,
Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton,
Washington 98057-3356; telephone (425) 227-1138; 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
(k) European Aviation Safety Agency (EASA) airworthiness
directive 2007-0243, dated September 4, 2007, also addresses the
subject of this AD.
Issued in Renton, Washington, on June 10, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-13566 Filed 6-16-08; 8:45 am]
BILLING CODE 4910-13-P