[Federal Register: August 7, 2008 (Volume 73, Number 153)]
[Proposed Rules]
[Page 45891-45893]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr07au08-15]
[[Page 45891]]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2008-0849; Directorate Identifier 2008-NM-080-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A310 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as: Two operators of A300 aircraft fitted with General
Electric (GE) CF6-50 engine series have reported cracks on the lower
side of Rib 5 in the pylon box. Investigations disclosed that these
cracks are due to the stresses resulting from the pressure applied by
the thrust reverser cowl bumpers. Cracking of the engine pylons could
result in reduced structural integrity of the engine support structure.
The proposed AD would require actions that are intended to address the
unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by September 8,
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 W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at http://
www.regulations.gov; or in person at the Docket Operations office
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 Operations 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: 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.
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-2008-0849;
Directorate Identifier 2008-NM-080-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 based on 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
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2008-0066, dated March 31, 2008 (referred to
after this as ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
Two operators of A300 aircraft fitted with General Electric (GE)
CF6-50 engine series have reported cracks on the lower side of Rib 5
in the pylon box.
The concerned area is similar on A310 aircraft fitted with GE
CF6-80A or CF6-80C series engines.
Investigations disclosed that these cracks are due to the
stresses resulting from the pressure applied by the thrust reverser
cowl bumpers.
As a result of the A310 Extended Service Goal (ESG) study, an
inspection programme of this area is required by this Airworthiness
Directive (AD).
A similar inspection programme is being contemplated for A300
and A300-600 series aircraft.
Cracking of the engine pylons could result in reduced structural
integrity of the engine support structure. Corrective actions include
modifying the Rib 5 in the pylon box. You may obtain further
information by examining the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Service Bulletins A310-54-2032, Revision 01,
dated October 8, 2007, and A310-54-2036, Revision 02, dated September
28, 2007. The actions described in this service information are
intended to correct the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 33 products of U.S. registry. We also estimate that
it would take about 8 work-hours per product to comply with the basic
requirements of this proposed AD. The average labor rate is $80 per
work-hour. Based on these figures, we estimate the cost of the proposed
AD on U.S. operators to be $21,120, or $640 per product, per inspection
cycle.
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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 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 this 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.
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 FAA amends Sec. 39.13 by adding the following new AD:
Airbus: Docket No. FAA-2008-0849; Directorate Identifier 2008-NM-
080-AD.
Comments Due Date
(a) We must receive comments by September 8, 2008.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A310-203, -204 and -304
airplanes, all serial numbers, certificated in any category;
excluding airplanes that have received Airbus Modification 11110
during production or that have been modified in service in
accordance with Airbus Service Bulletin A310-54-2032 (Airbus
Modification 11109).
Subject
(d) Air Transport Association (ATA) of America Code 54:
Nacelles/Pylons.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Two operators of A300 aircraft fitted with General Electric (GE)
CF6-50 engine series have reported cracks on the lower side of Rib 5
in the pylon box.
The concerned area is similar on A310 aircraft fitted with GE
CF6-80A or CF6-80C series engines.
Investigations disclosed that these cracks are due to the
stresses resulting from the pressure applied by the thrust reverser
cowl bumpers.
As a result of the A310 Extended Service Goal (ESG) study, an
inspection programme of this area is required by this Airworthiness
Directive (AD).
A similar inspection programme is being contemplated for A300
and A300-600 series aircraft.
Cracking of the engine pylons could result in reduced structural
integrity of the engine support structure. Corrective actions
include modifying the Rib 5 in the pylon box.
Actions and Compliance
(f) Unless already done, do the following actions.
(1) Perform a high frequency eddy current (HFEC) inspection and
a detailed visual inspection on the lower side of Rib 5 of the left-
hand and right-hand pylons, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A310-54-2036, Revision 02,
dated September 28, 2007. Do the inspections at the times specified
in paragraph (f)(1)(i) or (f)(1)(ii) of this AD, as applicable.
(i) For Model A310-203 and -204 airplanes: Inspect at the later
of the times specified in paragraphs (f)(1)(i)(A) and (f)(1)(i)(B)
of this AD.
(A) Prior to the accumulation of 40,000 total flight cycles or
60,000 total flight hours, whichever occurs first.
(B) Within 250 flight hours after the effective date of this AD.
(ii) For Model A310-304 airplanes: Inspect at the later of the
times specified in paragraphs (f)(1)(ii)(A) and (f)(1)(ii)(B) of
this AD.
(A) Prior to the accumulation of 35,000 total flight cycles or
60,000 total flight hours, whichever occurs first.
(B) Within 250 flight hours after the effective date of this AD.
(2) If no crack is found during any inspection required by
paragraph (f)(1) of this AD: Repeat the inspections thereafter at
intervals not to exceed 15,000 flight hours.
(3) If any crack is found during any inspection required by
paragraph (f)(1) of this AD: Before further flight, modify Rib 5 in
the pylon box in accordance with the Accomplishment Instructions of
Airbus Service Bulletins A310-54-2032, Revision 01, dated October 8,
2007. Accomplishment of this modification ends the repetitive
inspections required by this AD.
(4) Accomplishment of the HFEC and detailed visual inspections
before the effective date of this AD in accordance with Airbus
Service Bulletin A310-54-2036, Revision 01, dated September 14,
1999, meets the corresponding requirements of paragraph (f) of this
AD.
(5) Accomplishment of the modification before the effective date
of this AD in accordance with Airbus Service Bulletin A310-54-2032,
dated May 29, 1996, meets the corresponding requirements of
paragraph (f) of this AD.
(6) Submit the initial inspection results specified in Appendix
01 of Airbus Service Bulletin A310-54-2036, Revision 02, dated
September 28, 2007, at the time specified in paragraph (f)(6)(i) or
(f)(6)(ii) of this AD.
(i) If the inspections were done after the effective date of
this AD: Within 30 days after accomplishing the inspections required
by paragraph (f)(1) of this AD.
(ii) If the inspections were done prior to the effective date of
this AD: Within 30 days after the effective date of this AD.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: Although the MCAI allows further flight after cracks are
found during compliance with the required action, this AD requires
that you repair the crack(s) before further flight.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, 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.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from
[[Page 45893]]
a manufacturer or other source, use these actions if they are FAA-
approved. Corrective actions are considered FAA-approved if they are
approved by the State of Design Authority (or their delegated
agent). You are required to assure the product is airworthy before
it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act, the
Office of Management and Budget (OMB) has approved the information
collection requirements and has assigned OMB Control Number 2120-
0056.
Related Information
(h) Refer to MCAI EASA Airworthiness Directive 2008-0066, dated
March 31, 2008, and Airbus Service Bulletins A310-54-2032, Revision
01, dated October 8, 2007; and A310-54-2036, Revision 02, dated
September 28, 2007; for related information.
Issued in Renton, Washington, on July 29, 2008.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. E8-18210 Filed 8-6-08; 8:45 am]
BILLING CODE 4910-13-P