Document ID: FAA-2011-0035-0001
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Model A300 B4 601, B4 603, B4-605R, C4-605R Variant F, and F4-605R Airplanes, and A310-204 and -304 Airplanes
Posted Date: 2011-02-01T05:00Z

[Federal Register Volume 76, Number 21 (Tuesday, February 1, 2011)]
[Proposed Rules]
[Pages 5507-5510]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-2173]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0035; Directorate Identifier 2010-NM-110-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A300 B4-601, B4-603, B4-
605R, C4-605R Variant F, and F4-605R Airplanes, and A310-204 and -304 
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:

    Airbus, in the frame of the Extended Service Goal (ESG) 
exercise, has demonstrated by post-certification analysis that, 
among the types of yokes in service, one component on the CF6-80C2 
forward engine mounts (skinny cast yoke) does not meet the Design 
Service Goal (DSG) requirements.
    This condition, if not corrected, could result in a 
deterioration of the structural integrity of the forward engine 
mount.
* * * * *
    The unsafe condition is possible separation of the engine from the 
engine mount during flight. The proposed AD would require actions that 
are intended to address the unsafe condition described in the MCAI.

[[Page 5508]]

DATES: We must receive comments on this proposed AD by March 18, 2011.

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.
    For service information identified in this proposed AD, contact 
Airbus SAS--EAW (Airworthiness Office), 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; e-mail: account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue, SW., Renton, Washington. For information on the availability of 
this material at the FAA, call 425-227-1221.

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-2011-0035; 
Directorate Identifier 2010-NM-110-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 2010-0066, dated April 21, 2010 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Airbus, in the frame of the Extended Service Goal (ESG) 
exercise, has demonstrated by post-certification analysis that, 
among the types of yokes in service, one component on the CF6-80C2 
forward engine mounts (skinny cast yoke) does not meet the Design 
Service Goal (DSG) requirements.
    This condition, if not corrected, could result in a 
deterioration of the structural integrity of the forward engine 
mount.
    For the reasons described above, this AD requires operators to 
[perform an inspection to determine the part number of the forward 
engine mount skinny cast yokes,] perform a one time [detailed] 
inspection [for rupture] of the forward engine mount skinny cast 
yokes Part Number (P/N) 9383M43G08, 9383M43G09, 9383M43G10 and 
9383M43G11 of GE CF6-80C2 powered aeroplanes and to replace the 
affected skinny cast yokes with forged yokes.
    Upon replacement of the skinny cast yoke, the General Electric 
CF6-80C2 Service Bulletin (SB) 72-0222 [installation of a redesigned 
forward engine mount system] must be completed as a prerequisite.
    The unsafe condition is possible separation of the engine from the 
engine mount during flight. You may obtain further information by 
examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued All Operators Telexes A300-71A6029, including 
Appendices 01, 02, 03, and 04, dated March 30, 2010; and A310-71A2036, 
including Appendices 01, 02, 03, and 04, dated March 30, 2010. GE has 
issued CF6-80C2 Service Bulletin 72-0222, Revision 4, dated February 
29, 2000. 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 53 products of U.S. registry. We also estimate that 
it would take about 10 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Based on these figures, we estimate the cost of the proposed 
AD on U.S. operators to be $45,050, or $850 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 608 work-hours and require parts costing $322,000, for a 
cost of $373,680 per product. We have no way of determining the number 
of products that may need these actions.

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:

[[Page 5509]]

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, Incorporation by 
reference, 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-2011-0035; Directorate Identifier 2010-NM-
110-AD.

Comments Due Date

    (a) We must receive comments by March 18, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-
605R, C4-605R Variant F, and F4-605R airplanes, and A310-204 and -
304 airplanes; certificated in any category; powered by General 
Electric Model CF6-80C2 engines.

Subject

    (d) Air Transport Association (ATA) of America Code 71: 
Powerplant.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Airbus, in the frame of the Extended Service Goal (ESG) 
exercise, has demonstrated by post-certification analysis that, 
among the types of yokes in service, one component on the CF6-80C2 
forward engine mounts (skinny cast yoke) does not meet the Design 
Service Goal (DSG) requirements.
    This condition, if not corrected, could result in a 
deterioration of the structural integrity of the forward engine 
mount.
* * * * *
    The unsafe condition is possible separation of the engine from 
the engine mount during flight.

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Inspection and Corrective Actions

    (g) Within 400 flight cycles after the effective date of this 
AD, for each engine, inspect to determine the part number of the 
forward engine mounting yoke, in accordance with Airbus All 
Operators Telex A300-71A6029 or A310-71A2036, both dated March 30, 
2010, as applicable. A review of airplane maintenance records is 
acceptable in lieu of this inspection if the part number of the yoke 
can be conclusively determined from that review.
    (1) If the inspection required in paragraph (g) of this AD finds 
any mounting yoke is a skinny cast yoke having part number (P/N) 
9383M43G08, 9383M43G09, 9383M43G10, or 9383M43G11, do a detailed 
inspection of the yoke to determine if it is ruptured, in accordance 
with Airbus All Operators Telex A300-71A6029 or A310-71A2036, both 
dated March 30, 2010, as applicable.
    (i) If the mounting yoke is ruptured, before further flight, 
repair in accordance with a method approved by the FAA or the 
European Aviation Safety Agency (EASA) or its delegated agent.
    (ii) If the mounting yoke is not ruptured, within 7,000 flight 
cycles after the effective date of this AD replace the skinny cast 
yoke with a forged yoke, in accordance with Airbus All Operators 
Telex A300-71A6029 or A310-71A2036, both dated March 30, 2010, as 
applicable.
    (2) At the applicable time specified in paragraph (g)(2)(i) or 
(g)(2)(ii) of this AD, report to Airbus the findings of the 
inspection required by paragraph (g)(1) using Appendix 02 and 
Appendix 03, as applicable, of Airbus All Operators Telex A300-
71A6029 or A310-71A2036, both dated March 30, 2010, as applicable. 
Send the report to Laure Dupland, SEEE3; Customer Services; 
telephone +33 (0)5 61 18 20 24; fax +33 (0)5 61 93 36 14; e-mail 
laure.dupland@airbus.com.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (ii) If the inspection was done before the effective date of 
this AD: Submit the report within 30 days after the effective date 
of this AD.
    (h) Prior to or concurrent with the actions required by 
paragraph (g)(1)(ii), install a redesigned forward engine mount 
system in accordance with the Accomplishment Instructions of GE CF6-
80C2 Service Bulletin 72-0222, Revision 4, dated February 29, 2000.
    (i) As of the effective date of this AD, do not install any 
forward engine mount skinny cast yoke having P/N 9383M43G08, 
9383M43G09, 9383M43G10, or 9383M43G11, on any airplane.

FAA AD Differences

    Note 1:  This AD differs from the MCAI and/or service 
information as follows: No differences.

Other FAA AD Provisions

    (j) 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, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD.
    (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: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection

[[Page 5510]]

of information are mandatory. Comments concerning the accuracy of 
this burden and suggestions for reducing the burden should be 
directed to the FAA at: 800 Independence Ave., SW., Washington, DC 
20591, Attn: Information Collection Clearance Officer, AES-200.

Related Information

    (k) Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2010-0066, dated April 21, 2010; and the 
service information identified in Table 1 of this AD; for related 
information.

                      Table 1--Service Information
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     Service information          Revision                Date
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Airbus All Operators Telex    Original.......  March 30, 2010.
 A300-71A6029.
Airbus All Operators Telex    Original.......  March 30, 2010.
 A310-71A2036.
GE CF6-80C2 Service Bulletin  4..............  February 29, 2000.
 72-0222.
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    Issued in Renton, Washington, on January 25, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-2173 Filed 1-31-11; 8:45 am]
BILLING CODE 4910-13-P