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, 24356-24358 [2011-9678]

Download as PDF 24356 Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations Issued in Renton, Washington, on April 12, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. 1200 New Jersey Avenue, SE., Washington, DC. DEPARTMENT OF TRANSPORTATION 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: Federal Aviation Administration Discussion 14 CFR Part 39 We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on February 1, 2011 (76 FR 5507). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: [FR Doc. 2011–9674 Filed 4–29–11; 8:45 am] BILLING CODE 4910–13–P [Docket No. FAA–2011–0035; Directorate Identifier 2010–NM–110–AD; Amendment 39–16672; AD 2011–09–10] 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 Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: We are adopting a new airworthiness directive (AD) for the products listed above. This 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: SUMMARY: jlentini on DSKJ8SOYB1PROD with RULES 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. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective June 6, 2011. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of June 6, 2011. ADDRESSES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, VerDate Mar<15>2010 16:25 Apr 29, 2011 Jkt 223001 FOR FURTHER INFORMATION CONTACT: 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. Comments We gave the public the opportunity to participate in developing this AD. We considered the comment received. FedEx supports the NPRM. Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD as proposed. Differences Between This AD and the MCAI or Service Information We have reviewed the MCAI and related service information and, in PO 00000 Frm 00014 Fmt 4700 Sfmt 4700 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 required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance We estimate that this AD will affect 53 products of U.S. registry. We also estimate that it will take about 10 workhours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the 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: 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 This AD will not have federalism implications under Executive Order 13132. This AD will 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. E:\FR\FM\02MYR1.SGM 02MYR1 Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations For the reasons discussed above, I certify that this AD: 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 AD and placed it in the AD docket. Subject (d) Air Transport Association (ATA) of America Code 71: Powerplant. 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 the NPRM, 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. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: ■ 2011–09–10 Airbus: Amendment 39–16672. Docket No. FAA–2011–0035; Directorate Identifier 2010–NM–110–AD. Effective Date (a) This airworthiness directive (AD) becomes effective June 6, 2011. jlentini on DSKJ8SOYB1PROD with RULES 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. VerDate Mar<15>2010 16:25 Apr 29, 2011 Jkt 223001 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. PO 00000 Frm 00015 Fmt 4700 Sfmt 4700 24357 (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) of this AD, 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. In accordance with 14 CFR 39.19, send your request to your principal inspector or local Flight Standards District Office, as appropriate. If sending information directly to the International Branch, send it 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. Information may be e-mailed to: 9ANM-116-AMOC-REQUESTS@faa.gov. 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 of information are mandatory. Comments E:\FR\FM\02MYR1.SGM 02MYR1 24358 Federal Register / Vol. 76, No. 84 / Monday, May 2, 2011 / Rules and Regulations 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 Service information Revision Date Airbus All Operators Telex A300–71A6029 ...................................................................... Airbus All Operators Telex A310–71A2036 ...................................................................... GE CF6–80C2 Service Bulletin 72–0222 ......................................................................... Original .......................................... Original .......................................... 4 .................................................... March 30, 2010. March 30, 2010. February 29, 2000. Material Incorporated by Reference (l) You must use the service information contained in table 2 of this AD, as applicable, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) For service information identified in this 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.airwortheas@airbus.com; Internet http:// www.airbus.com. (3) You may review copies of the 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. (4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go to: http://www.archives.gov/federal_register/ code_of_federal_regulations/ibr_ locations.html. TABLE 2—MATERIAL INCORPORATED BY REFERENCE Service information Revision Date Airbus All Operators Telex A300–71A6029, including Appendices 01, 02, 03, and 04 .. Airbus All Operators Telex A310–71A2036, including Appendices 01, 02, 03, and 04 .. GE CF6–80C2 Service Bulletin 72–0222 ......................................................................... Original .......................................... Original .......................................... 4 .................................................... March 30, 2010. March 30, 2010. February 29, 2000. Issued in Renton, Washington, on April 13, 2011. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–9678 Filed 4–29–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–1207; Directorate Identifier 2010–NM–140–AD; Amendment 39–16680; AD 2011–09–18] * * * * We are issuing this AD to require actions to correct the unsafe condition on these products. Airworthiness Directives; DassaultAviation Model FALCON 7X Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. jlentini on DSKJ8SOYB1PROD with RULES AGENCY: 16:25 Apr 29, 2011 Jkt 223001 This AD becomes effective June 6, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of June 6, 2011. DATES: You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC. ADDRESSES: We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct VerDate Mar<15>2010 Following investigation of an in service event, it has been determined that in case a short circuit occurs on a weight-on-wheels (WOW) proximity sensor wiring, both circuit breakers that supply power to that wiring will trip, causing simultaneous de-power of all WOW proximity sensors of that part of the system. The loss of the corresponding WOW information would lead to untimely inhibition of warnings that could compromise the pilot capacity to react to abnormal or failure landing conditions. * RIN 2120–AA64 SUMMARY: an unsafe condition on an aviation product. The MCAI describes the unsafe condition as: PO 00000 Frm 00016 Fmt 4700 Sfmt 4700 Tom Rodriguez, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1137; fax (425) 227–1149. SUPPLEMENTARY INFORMATION: FOR FURTHER INFORMATION CONTACT: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on December 30, 2010 (75 FR 82327). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: Following investigation of an in service event, it has been determined that in case a short circuit occurs on a weight-on-wheels (WOW) proximity sensor wiring, both circuit breakers that supply power to that wiring will trip, causing simultaneous de-power of all WOW proximity sensors of that part of the system. The loss of the corresponding WOW information would lead to untimely inhibition of warnings that could compromise the pilot capacity to react to abnormal or failure landing conditions. This AD requires the modification of the WOW System to improve its robustness against short circuit of the proximity sensors wiring by adding dedicated fuses to each E:\FR\FM\02MYR1.SGM 02MYR1

Agencies

[Federal Register Volume 76, Number 84 (Monday, May 2, 2011)]
[Rules and Regulations]
[Pages 24356-24358]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-9678]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0035; Directorate Identifier 2010-NM-110-AD; 
Amendment 39-16672; AD 2011-09-10]
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), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. This 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. We are issuing this AD to require actions 
to correct the unsafe condition on these products.

DATES: This AD becomes effective June 6, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 6, 2011.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue, SE., Washington, DC.

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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on February 1, 2011 (76 
FR 5507). That NPRM proposed 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. FedEx supports the NPRM.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD as proposed.

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 required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a NOTE within the AD.

Costs of Compliance

    We estimate that this AD will affect 53 products of U.S. registry. 
We also estimate that it will take about 10 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD to the 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: 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

    This AD will not have federalism implications under Executive Order 
13132. This AD will 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.

[[Page 24357]]

    For the reasons discussed above, I certify that this AD:
    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 AD and placed it in the AD docket.

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 the NPRM, 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by adding the following new AD:

2011-09-10 Airbus: Amendment 39-16672. Docket No. FAA-2011-0035; 
Directorate Identifier 2010-NM-110-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective June 6, 
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) of this AD, 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. In accordance with 14 CFR 
39.19, send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Branch, send it 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. 
Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
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 of information are mandatory. Comments

[[Page 24358]]

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
------------------------------------------------------------------------
     Service information           Revision                Date
------------------------------------------------------------------------
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.
------------------------------------------------------------------------

Material Incorporated by Reference

    (l) You must use the service information contained in table 2 of 
this AD, as applicable, to do the actions required by this AD, 
unless the AD specifies otherwise.
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) For service information identified in this 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.
    (3) You may review copies of the 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.
    (4) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

               Table 2--Material Incorporated by Reference
------------------------------------------------------------------------
     Service information           Revision                Date
------------------------------------------------------------------------
Airbus All Operators Telex     Original........  March 30, 2010.
 A300-71A6029, including
 Appendices 01, 02, 03, and
 04.
Airbus All Operators Telex     Original........  March 30, 2010.
 A310-71A2036, including
 Appendices 01, 02, 03, and
 04.
GE CF6-80C2 Service Bulletin   4...............  February 29, 2000.
 72-0222.
------------------------------------------------------------------------


    Issued in Renton, Washington, on April 13, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-9678 Filed 4-29-11; 8:45 am]
BILLING CODE 4910-13-P