[Federal Register Volume 73, Number 153 (Thursday, August 7, 2008)]
[Proposed Rules]
[Pages 45891-45893]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: E8-18210]



[[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

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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