Airworthiness Directives; Airbus Airplanes, 5726-5728 [2012-2622]

Download as PDF 5726 Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules (d) Subject (k) Other FAA AD Provisions Air Transport Association (ATA) of America Code 53: Fuselage. 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. 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: 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. Information may be emailed 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 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. (e) Reason This AD was prompted by reports of cracks underneath the passenger door in a butt-joint on the forward fuselage of an F.28 Mark 0100 airplane. We are issuing this AD to detect and correct cracks on the butt-joint on the forward fuselage, which could result in explosive decompression and consequent loss of control of the airplane. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Inspection Before the accumulation of 20,000 total flight cycles, or within 180 flight cycles after the effective date of this AD, whichever occurs later, do a low frequency eddy current inspection of the forward fuselage butt-joints for cracks, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–53–115, dated June 16, 2011. Repeat the inspection thereafter at intervals not to exceed 1,000 flight cycles. Doing the temporary repair in paragraph (h) of this AD is terminating action for the repetitive inspections required by this paragraph. The temporary repair can also be accomplished if no cracking is found. (h) Temporary Repair If any cracking is found during any inspection required by paragraph (g) of this AD, before further flight, do a temporary repair, in accordance with the Accomplishment Instructions of Fokker Service Bulletin SBF100–53–115, dated June 16, 2011. Doing the temporary repair is terminating action for the repetitive inspections required by paragraph (g) of this AD. (i) Permanent Repair Within 10,000 flight cycles after installing the temporary repair as required by paragraph (h) of this AD, install a permanent repair using a method approved by the Manager, International Branch, ANM 116, Transport Airplane Directorate, FAA. tkelley on DSK3SPTVN1PROD with PROPOSALS (j) Reporting Submit a report of the findings (both positive and negative), to Fokker Services B.V., Technical Services Dept., P.O. Box 231, 2150 AE Nieuw-Vennep, the Netherlands, using the reports form of Fokker Service Bulletin SBF100–53–115, dated June 16, 2011, of the inspection required by paragraph (g) of this AD, at the applicable time specified in paragraph (j)(1) or (j)(2) of this AD. (1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection. (2) 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. VerDate Mar<15>2010 15:45 Feb 03, 2012 Jkt 226001 DEPARTMENT OF TRANSPORTATION (l) Related Information Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2011–0115, dated June 17, 2011; and Fokker Service Bulletin SBF100–53–115, dated June 16, 2011; for related information. Issued in Renton, Washington, on January 12, 2012. Michael J. Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–2618 Filed 2–3–12; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00010 Fmt 4702 Sfmt 4702 Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0041; Directorate Identifier 2011–NM–167–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes. This proposed AD was prompted by analysis that in a specific failure case of the upper primary attachment of the trimmable horizontal stabilizer actuator (THSA); the THSA upper secondary attachment would engage because it could only withstand the loads for a limited period of time. This proposed AD would require installation of three secondary retention plates for the gimbal bearings on the THSA upper primary attachment. We are proposing this AD to prevent failure of the secondary load path, which could result in loss of control of the airplane. DATES: We must receive comments on this proposed AD by March 22, 2012. ADDRESSES: You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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 W12–140, 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 https://www.airbus.com. You may review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. SUMMARY: E:\FR\FM\06FEP1.SGM 06FEP1 Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules 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 https:// 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: tkelley on DSK3SPTVN1PROD with PROPOSALS 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–2012–0041; Directorate Identifier 2011–NM–167–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 https:// 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 2011–0112, dated June 15, 2011 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: A specific failure case of the THSA [trimmable horizontal stabilizer actuator] upper primary attachment, which may result in a loading of the upper secondary attachment, has been identified by analysis. Primary load path failure can be caused by bearing migration from the upper attachment gimbal by failure or loss of a retention bolt. VerDate Mar<15>2010 15:45 Feb 03, 2012 Jkt 226001 In case of failure of the THSA upper primary attachment, the THSA upper secondary attachment would engage. Because the upper attachment secondary load path can only withstand the loads for a limited period of time, the condition where it would be engaged could lead, if not detected and corrected, to the failure of the secondary load path, which would likely result in loss of control of the aeroplane. For the reasons explained above, this [EASA] AD requires installation of three secondary retention plates for the gimbal bearings on the THSA upper primary attachment. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued Mandatory Service Bulletin A300–27–0204, dated March 11, 2011. 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. Costs of Compliance Based on the service information, we estimate that this proposed AD would affect about 15 products of U.S. registry. We also estimate that it would take about 2 work-hours per product to comply with the basic requirements of this proposed AD. The average labor rate is $85 per work-hour. Required parts would cost about $6,541 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 parts. 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 $100,665, or $6,711 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 PO 00000 Frm 00011 Fmt 4702 Sfmt 4702 5727 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 affect intrastate aviation in Alaska; and 4. 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. E:\FR\FM\06FEP1.SGM 06FEP1 5728 § 39.13 Federal Register / Vol. 77, No. 24 / Monday, February 6, 2012 / Proposed Rules [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Airbus: Docket No. FAA–2012–0041; Directorate Identifier 2011–NM–167–AD. (a) Comments Due Date We must receive comments by March 22, 2012. (b) Affected ADs None. (c) Applicability This AD applies to all Airbus Model A300 B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4–203 airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 27: Flight controls. (e) Reason This AD was prompted by analysis that in a specific failure case of the upper primary attachment of the trimmable horizontal stabilizer actuator (THSA); the THSA upper secondary attachment would engage because it could only withstand the loads for a limited period of time. We are issuing this AD to prevent failure of the secondary load path, which could result in loss of control of the airplane. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. tkelley on DSK3SPTVN1PROD with PROPOSALS (g) Actions Within 30 months after the effective date of this AD, install 3 retention plates for the gimbal bearings on the THSA upper primary attachment, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–27–0204, dated March 11, 2011. (h) Other FAA AD Provisions 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 emailed 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 VerDate Mar<15>2010 15:45 Feb 03, 2012 Jkt 226001 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. (i) Related Information Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2011–0112, dated June 15, 2011; and Airbus Mandatory Service Bulletin A300–27–0204, dated March 11, 2011; for related information. Issued in Renton, Washington, on January 23, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–2622 Filed 2–3–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012 0040; Directorate Identifier 2011–NM–121–AD] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; all Model A300 B4–600, B4–600R, and F4– 600R series airplanes, and Model C4– 605R Variant F airplanes (collectively called A300–600 series airplanes). This proposed AD was prompted by reports of an inoperative fire shut-off valve (FSOV) as a result of damage due to over-length of the bonding lead. This proposed AD would require a one-time detailed inspection for length of the FSOV bonding leads and for contact or chafing of the wires, and corrective actions, if necessary. We are proposing this AD to detect and correct contact or chafing of wires and bonding leads which, if not detected could be a source of sparks in the wing trailing edge, and could lead to an uncontrolled engine fire. SUMMARY: We must receive comments on this proposed AD by March 22, 2012. DATES: PO 00000 Frm 00012 Fmt 4702 Sfmt 4702 You may send comments by any of the following methods: • Federal eRulemaking Portal: Go to https://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 W12–140, 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; email: account.airworth-eas@airbus.com; Internet https://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. ADDRESSES: Examining the AD Docket You may examine the AD docket on the Internet at https:// 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–2012–0040; Directorate Identifier 2011–NM–121–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, E:\FR\FM\06FEP1.SGM 06FEP1

Agencies

[Federal Register Volume 77, Number 24 (Monday, February 6, 2012)]
[Proposed Rules]
[Pages 5726-5728]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-2622]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0041; Directorate Identifier 2011-NM-167-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Airbus Model A300 B2-1C, B2K-3C, B2-203, B4-2C, B4-103, and B4-203 
airplanes. This proposed AD was prompted by analysis that in a specific 
failure case of the upper primary attachment of the trimmable 
horizontal stabilizer actuator (THSA); the THSA upper secondary 
attachment would engage because it could only withstand the loads for a 
limited period of time. This proposed AD would require installation of 
three secondary retention plates for the gimbal bearings on the THSA 
upper primary attachment. We are proposing this AD to prevent failure 
of the secondary load path, which could result in loss of control of 
the airplane.

DATES: We must receive comments on this proposed AD by March 22, 2012.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to https://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 W12-140, 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 https://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington.

[[Page 5727]]

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 https://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-2012-0041; 
Directorate Identifier 2011-NM-167-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 https://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 2011-0112, dated June 15, 2011 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    A specific failure case of the THSA [trimmable horizontal 
stabilizer actuator] upper primary attachment, which may result in a 
loading of the upper secondary attachment, has been identified by 
analysis.
    Primary load path failure can be caused by bearing migration 
from the upper attachment gimbal by failure or loss of a retention 
bolt.
    In case of failure of the THSA upper primary attachment, the 
THSA upper secondary attachment would engage. Because the upper 
attachment secondary load path can only withstand the loads for a 
limited period of time, the condition where it would be engaged 
could lead, if not detected and corrected, to the failure of the 
secondary load path, which would likely result in loss of control of 
the aeroplane.
    For the reasons explained above, this [EASA] AD requires 
installation of three secondary retention plates for the gimbal 
bearings on the THSA upper primary attachment.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A300-27-0204, dated 
March 11, 2011. 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.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 15 products of U.S. registry. We also estimate that 
it would take about 2 work-hours per product to comply with the basic 
requirements of this proposed AD. The average labor rate is $85 per 
work-hour. Required parts would cost about $6,541 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 
parts. 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 $100,665, or $6,711 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 affect intrastate aviation in Alaska; and
    4. 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.

[[Page 5728]]

Sec.  39.13  [Amended]

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

Airbus: Docket No. FAA-2012-0041; Directorate Identifier 2011-NM-
167-AD.

(a) Comments Due Date

    We must receive comments by March 22, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Airbus Model A300 B2-1C, B2K-3C, B2-203, 
B4-2C, B4-103, and B4-203 airplanes, certificated in any category.

(d) Subject

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

(e) Reason

    This AD was prompted by analysis that in a specific failure case 
of the upper primary attachment of the trimmable horizontal 
stabilizer actuator (THSA); the THSA upper secondary attachment 
would engage because it could only withstand the loads for a limited 
period of time. We are issuing this AD to prevent failure of the 
secondary load path, which could result in loss of control of the 
airplane.

(f) Compliance

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

(g) Actions

    Within 30 months after the effective date of this AD, install 3 
retention plates for the gimbal bearings on the THSA upper primary 
attachment, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A300-27-0204, dated March 11, 
2011.

(h) Other FAA AD Provisions

    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 emailed 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.

(i) Related Information

    Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2011-0112, dated June 15, 2011; and Airbus 
Mandatory Service Bulletin A300-27-0204, dated March 11, 2011; for 
related information.

    Issued in Renton, Washington, on January 23, 2012.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-2622 Filed 2-3-12; 8:45 am]
BILLING CODE 4910-13-P
This site is protected by reCAPTCHA and the Google Privacy Policy and Terms of Service apply.