Document ID: FAA-2008-0979-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Airbus Model A300-600 Airplanes
Posted Date: 2008-09-17T04:00Z

[Federal Register: September 17, 2008 (Volume 73, Number 181)]
[Proposed Rules]               
[Page 53768-53770]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr17se08-37]                         

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2008-0979; Directorate Identifier 2008-NM-079-AD]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A300-600 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:

    Further to initial qualification tests of the spoiler actuators 
currently installed in position No. 3 to 7 on A300-600 and A300-
600ST aircraft fleet, a life limit [of 55,750 flight hours] has been 
defined by the actuator manufacturer. Initially, this life limit had 
no repercussions, as it was situated well beyond the initial Design 
Service Goal (DSG) of the aircraft. However, due to the Extended 
Service Goal (ESG) activities, the spoiler actuator life limit can 
be reached in service, and therefore the spoiler actuators must be 
replaced before exceeding this limit.
    In order to mitigate the risk to have aircraft on which the 
three hydraulic circuits would be impacted by affected spoiler 
actuators, which could result in the loss of controllability of the 
aircraft, this Airworthiness Directive (AD) requires actions to 
ensure that at least the level of safety of one hydraulic circuit 
will be restored within an acceptable timeframe.
* * * * *

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 October 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 W12-40, 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-2008-0979; 
Directorate Identifier 2008-NM-079-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 2008-0058, dated March 20, 2008 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Further to initial qualification tests of the spoiler actuators 
currently installed in position No. 3 to 7 on A300-600 and A300-
600ST aircraft fleet, a life limit [of 55,750 flight hours] has been 
defined by the actuator manufacturer. Initially, this life limit had 
no repercussions, as it was situated well beyond the initial Design 
Service Goal (DSG) of the aircraft. However, due to the Extended 
Service Goal (ESG) activities, the spoiler actuator life limit can 
be reached in service, and therefore the spoiler actuators must be 
replaced before exceeding this limit.
    In order to mitigate the risk to have aircraft on which the 
three hydraulic circuits would be impacted by affected spoiler 
actuators, which could result in the loss of controllability of the 
aircraft, this Airworthiness Directive (AD) requires actions to 
ensure that at least the level of safety of one hydraulic circuit 
will be restored within an acceptable timeframe.

[[Page 53769]]

    EASA AD 2007-0245, issued on 05 September 2007 as an interim 
action, is superseded by the present [EASA] AD.

Corrective actions include replacing the spoiler actuator with a 
serviceable unit. You may obtain further information by examining the 
MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletins A300-27-6060, including 
Appendix 01, dated February 18, 2008, and A300-27A6062, including 
Appendix 01, dated July 6, 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 135 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. Required parts would cost about $32,000 per product. Where 
the service information lists required parts costs that are covered 
under warranty, we have assumed that there will be no charge for these 
costs. As we do not control warranty coverage for affected parties, 
some parties may incur costs higher than estimated here. Based on these 
figures, we estimate the cost of the proposed AD on U.S. operators to 
be $4,406,400, or $32,640 per product.

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-2008-0979; Directorate Identifier 2008-NM-
079-AD.

Comments Due Date

    (a) We must receive comments by October 17, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300-600 airplanes, all 
serial numbers, certificated in any category; on which Smith spoiler 
actuators having part number (P/N) P376A0002-05, -06, -07, or -09, 
or P/N P725A0001-00 are installed.

Subject

    (d) Air Transport Association (ATA) of America Code 27: Flight 
controls.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    Further to initial qualification tests of the spoiler actuators 
currently installed in position No. 3 to 7 on A300-600 and A300-
600ST aircraft fleet, a life limit [of 55,750 flight hours] has been 
defined by the actuator manufacturer. Initially, this life limit had 
no repercussions, as it was situated well beyond the initial Design 
Service Goal (DSG) of the aircraft. However, due to the Extended 
Service Goal (ESG) activities, the spoiler actuator life limit can 
be reached in service, and therefore the spoiler actuators must be 
replaced before exceeding this limit.
    In order to mitigate the risk to have aircraft on which the 
three hydraulic circuits would be impacted by affected spoiler 
actuators, which could result in the loss of controllability of the 
aircraft, this Airworthiness Directive (AD) requires actions to 
ensure that at least the level of safety of one hydraulic circuit 
will be restored within an acceptable timeframe.
    EASA AD 2007-0245, issued on 05 September 2007 as an interim 
action, is superseded by the present [EASA] AD.
Corrective actions include replacing the spoiler actuator with a 
serviceable unit.

Actions and Compliance

    (f) Unless already done: Within 700 flight hours after the 
effective date of this AD, do the following actions.
    (1) Identify the total flight hours accumulated on each spoiler 
actuator at positions 3 through 7 on the left- and right-hand sides 
of the airplane (FIN 22CP/23CP, 24CP/25CP, 26CP/27CP, 60CP/61CP and

[[Page 53770]]

62CP/63CP), in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-27A6062, dated July 6, 2007.
    (2) For airplanes on which the status of any spoiler actuator is 
unknown (unknown number of accumulated flight hours, unknown date of 
manufacture and/or unknown serial number) the actuator must be 
considered as having exceeded 55,750 total flight hours.
    (3) For airplanes on which all three hydraulic circuits have a 
spoiler actuator that has accumulated or exceeds 55,000 total flight 
hours: Before the accumulation of 55,750 total flight hours or 
within 700 flight hours after the effective date of this AD, 
whichever occurs later, on at least one hydraulic circuit, 
interchange the spoiler actuator with a serviceable unit from 
another hydraulic circuit, or replace the spoiler actuator with a 
serviceable unit, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A300-27-6060, dated February 18, 2008.
    (4) For airplanes on which the actions required by paragraph 
(f)(1) of this AD, and, as applicable, paragraph (f)(3) of this AD 
have been accomplished, each airplane must continue to have at least 
one hydraulic circuit fitted with spoiler actuators that do not 
exceed 55,750 total flight hours.

    Note 1: For the purposes of this AD, a serviceable unit is a 
unit that has accumulated less than 55,750 flight hours.

    (5) The operator must not interchange or replace spoiler 
actuators on more than two hydraulic circuits at the same time. This 
will mitigate the risk of having a malfunction on the three 
hydraulic systems at the same time.

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows:
    (1) This AD does not include the reporting requirement specified 
in paragraph (1) of the MCAI. The MCAI carried this requirement 
forward from European Aviation Safety Agency (EASA) Airworthiness 
Directive 2007-0245, dated September 5, 2007. We previously 
determined that no action was required on our part regarding EASA AD 
2007-0245.

Other FAA AD Provisions

    (g) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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 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 2008-0058, dated 
March 20, 2008; and Airbus Service Bulletins A300-27-6060, dated 
February 18, 2008; and A300-27A6062, dated July 6, 2007; for related 
information.

    Issued in Renton, Washington, on September 9, 2008.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-21724 Filed 9-16-08; 8:45 am]

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