Document ID: FAA-2007-0396-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives; Airbus Model A330-200, A330-300, A340- 200, and A340-300 Series Airplanes
Posted Date: 2008-01-10T05:00Z

[Federal Register: January 10, 2008 (Volume 73, Number 7)]
[Proposed Rules]               
[Page 1842-1844]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr10ja08-14]                         

========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains notices to the public of 
the proposed issuance of rules and regulations. The purpose of these 
notices is to give interested persons an opportunity to participate in 
the rule making prior to the adoption of the final rules.

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[[Page 1842]]

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2007-0396; Directorate Identifier 2007-NM-282-AD]
RIN 2120-AA64

 
Airworthiness Directives; Airbus Model A330-200, A330-300, A340-
200, and A340-300 Series Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

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:

    One A320 operator has reported a disbond on the composite rudder 
control rod. Investigations conducted by the supplier revealed that 
this disbond is due to an incorrect low volume of resin in the fibre 
composite. The supplier and AIRBUS have confirmed that some rudder 
control rods installed on A330 and A340-200/-300 aircraft before 
delivery or delivered as spare are also affected by this defect. 
Rudder control rod rupture can lead, in the worst case, in 
combination with a yaw damper runaway to an unsafe condition.

* * * * *
    The unsafe condition is reduced control of the airplane. 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 February 11, 
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: 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-2007-0396; 
Directorate Identifier 2007-NM-282-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 2007-0246, dated September 5, 2007 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    One A320 operator has reported a disbond on the composite rudder 
control rod. Investigations conducted by the supplier revealed that 
this disbond is due to an incorrect low volume of resin in the fibre 
composite. The supplier and AIRBUS have confirmed that some rudder 
control rods installed on A330 and A340-200/-300 aircraft before 
delivery or delivered as spare are also affected by this defect. 
Rudder control rod rupture can lead, in the worst case, in 
combination with a yaw damper runaway to an unsafe condition.
    In order to prevent such situation, this Airworthiness Directive 
(AD) requires a one time detailed visual inspection to identify the 
affected rods and to replace those affected by this issue.

    The unsafe condition is reduced control of the airplane. You may 
obtain further information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued Service Bulletins A330-27-3157 and A340-27-4156, 
both dated August 8, 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

[[Page 1843]]

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 8 products of U.S. registry. We also estimate that 
it would take about 6 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $80 per 
work-hour. Labor costs may be covered under warranty as described in 
the service information. Based on these figures, we estimate the cost 
of the proposed AD on U.S. operators to be $3,840, or $480 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-2007-0396; Directorate Identifier 2007-NM-
282-AD.

Comments Due Date

    (a) We must receive comments by February 11, 2008.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A330-200, A330-300, A340-
200, and A340-300 series airplanes, certificated in any category, 
all certified models, having manufacturing serial numbers (MSNs) as 
specified in paragraphs (c)(1) and (c)(2) of this AD.
    (1) For Model A330-200 and A330-300 series airplanes: MSN 0315, 
0323, 0333, 0337, 0338, 0342, 0344, 0346, 0349, 0350, 0351, 0356, 
0357, 0370, 0375, 0388, 0389, 0398, 0400, 0404, 0407, 0408, 0412, 
0427, 0432, 0454, 0493 and 0539.
    (2) For Model A340-200 and A340-300 series airplanes: MSN 0318, 
0319, 0321, 0325, 0327, 0329, 0331, 0332, 0335, 0347, 0352, 0354, 
0355, 0359, 0363, 0367, 0373, 0374, 0377, 0378, 0379, 0381, 0385, 
0387, 0390, 0395, 0399, 0411, 0413, 0415, 0433, 0434, 0435, 0450 and 
0474.

Subject

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

Reason

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

    One A320 operator has reported a disbond on the composite rudder 
control rod. Investigations conducted by the supplier revealed that 
this disbond is due to an incorrect low volume of resin in the fibre 
composite. The supplier and AIRBUS have confirmed that some rudder 
control rods installed on A330 and A340-200/-300 aircraft before 
delivery or delivered as spare are also affected by this defect. 
Rudder control rod rupture can lead, in the worst case, in 
combination with a yaw damper runaway to an unsafe condition.
    In order to prevent such situation, this Airworthiness Directive 
(AD) requires a one time detailed visual inspection to identify the 
affected rods and to replace those affected by this issue.

    The unsafe condition is reduced control of the airplane.

Actions and Compliance

    (f) Unless already done, do the following actions.
    (1) Within 600 flight hours after the effective date of this AD, 
identify the part number (P/N) and serial number (S/N) of all rudder 
control rods installed on the subject airplanes; in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A330-27-
3157 or A340-27-4156, both dated August 8, 2007, as applicable.
    (2) If the P/N and S/N of any rudder control rod identified in 
paragraph (f)(1) of this AD is not identified in Batch 1, Batch 2a, 
or Batch 2b of Figure 3 of Airbus Service Bulletin A330-27-3157 or 
A340-27-4156, both dated August 8, 2007, no further action is 
required for that control rod, except as provided by paragraph 
(f)(6) of this AD.
    (3) If the P/N and S/N of any rudder control rod identified in 
paragraph (f)(1) of this AD is identified in Batch 1 of Figure 3 of 
Airbus Service Bulletin A330-27-3157 or A340-27-4156, both dated 
August 8, 2007: Within 18 months after the identification required 
by paragraph (f)(1) of this AD, replace the affected rudder control 
rod with a new rudder control rod, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-27-3157 
or A340-27-4156, as applicable.
    (4) If the P/N and S/N of any rudder control rod identified in 
paragraph (f)(1) of this AD is identified in Batch 2a of Figure 3 of 
Airbus Service Bulletin A330-27-3157 or A340-27-4156, both dated 
August 8, 2007: Within 1,400 flight hours after the identification 
required by paragraph (f)(1) of this AD, replace the affected 
control rod with a new rudder control rod, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-27-3157 
or A340-27-4156, as applicable.
    (5) If the P/N and S/N of any rudder control rod identified in 
paragraph (f)(1) of this AD is identified in Batch 2b of Figure 3 of 
Airbus Service Bulletin A330-27-3157 or A340-27-4156, both dated 
August 8, 2007, do the actions described in paragraph (f)(5)(i) or 
(f)(5)(ii) of this AD, as applicable, at the compliance time 
specified in paragraph (f)(5)(i) or (f)(5)(ii), as applicable.
    (i) For any rudder control rod having P/N 22205-08 and S/N 
1000094651: Within 600

[[Page 1844]]

flight hours after the identification required by paragraph (f)(1) 
of this AD, replace the rudder control rod with a new rudder control 
rod, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A330-27-3157 or A340-27-4156, both dated August 8, 
2007, as applicable.
    (ii) For all rudder control rods not identified in paragraph 
(f)(5)(i) of this AD: Within 6 months after the identification 
required by paragraph (f)(1) of this AD, replace the rudder control 
rods with new rudder control rods, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A330-27-3157 
or A340-27-4156, both dated August 8, 2007, as applicable.
    (6) As of the effective date of this AD, no person may install, 
on any airplane, any rudder control rod unit having a P/N and S/N 
identified in Batch 1, Batch 2a, or Batch 2b of Figure 3 of Airbus 
Service Bulletin A330-27-3157 or A340-27-4156, both dated August 8, 
2007.

FAA AD Differences

    Note: This AD differs from the MCAI and/or service information 
as follows: No differences.

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: 
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.
    (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 2007-0246, dated 
September 5, 2007; Airbus Service Bulletin A330-27-3157, dated 
August 8, 2007; and Airbus Service Bulletin A340-27-4156, dated 
August 8, 2007; for related information.

    Issued in Renton, Washington, on December 21, 2007.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
 [FR Doc. E8-250 Filed 1-9-08; 8:45 am]

BILLING CODE 4910-13-P