Airworthiness Directives; Airbus Airplanes, 79560-79563 [2011-32845]

Download as PDF 79560 Federal Register / Vol. 76, No. 246 / Thursday, December 22, 2011 / Proposed Rules Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Airbus: Docket No. FAA–2012–1324; Directorate Identifier 2011–NM–104–AD. (a) Comments Due Date We must receive comments by February 6, 2012. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A300 B4– 601, B4–603, B4–620, B4–622, B4–605R, B4– 622R, F4–605R, F4–622R, and C4–605R Variant F airplanes; and Model A310–203, –204, –221, –222, –304, –322, –324, and –325 airplanes; certificated in any category; all certificated models, all manufacturer serial numbers. (d) Subject Air Transport Association (ATA) of America Code 52: Doors. (e) Reason This AD was prompted by a report of a crack in the forward cargo door selector valve pipe located in the avionics bay opposite to line replaceable unit racking. We are issuing this AD to prevent cracking in the forward cargo door selector valve pipe which could impact the 90 VU avionics line replaceable unit, and could result in multiple computer failures, affecting flight safety. (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) Replacement Except as provided by paragraph (h) of this AD: Within 30 months or 6,000 flight hours after the effective date of this AD, whichever occurs first, replace the aluminum high pressure pipe having part number (P/N) A5231006100300 with a new pipe made of corrosion resistant stainless steel having P/N A5231007000600, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–52–6065, Revision 01, dated July 5, 2010 (for Model A300 B4–600 series airplanes); or A310–52– 2067, Revision 01, dated July 5, 2010 (for Model A310 series airplanes). (i) Parts Installation DEPARTMENT OF TRANSPORTATION As of the effective date of this AD, no person may install an aluminum high pressure pipe having P/N A5231006100300, on any airplane. (j) Credit for Actions Accomplished in Accordance With Previous Service Information Replacements done before the effective date of this AD in accordance with Airbus Mandatory Service Bulletins A300–52–6065, dated July 9, 2002 (for Model A300–600 series airplanes); and A310–52–2067, dated July 9, 2002 (for Model A310 series airplanes); are acceptable for compliance with the requirements of paragraph (g) of this AD. The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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. (l) Related Information jlentini on DSK4TPTVN1PROD with PROPOSALS (h) Exception Any airplane that has incorporated Airbus Modification 12464 in production has the new P/N A5231007000600 installed and is therefore compliant with the requirements of paragraph (g) of this AD. If the high pressure pipe has been replaced with P/N A5231006100300 in service after delivery of the airplane, replace the high pressure pipe in accordance with paragraph (g) of this AD within the times specified in paragraph (g) of this AD. Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2011–0085, dated May 12, 2011 (corrected May 31, 2011); Airbus Mandatory Service Bulletin A300–52–6065, Revision 01, dated July 5, 2010; and Airbus Mandatory Service Bulletin A310–52–2067, Revision 01, dated July 5, 2010; for related information. Issued in Renton, Washington, on December 14, 2011. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. VerDate Mar<15>2010 19:15 Dec 21, 2011 Jkt 226001 [FR Doc. 2011–32844 Filed 12–21–11; 8:45 am] PO 00000 Frm 00013 Fmt 4702 Sfmt 4702 14 CFR Part 39 [Docket No. FAA–2011–1323; Directorate Identifier 2010–NM–212–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 Model A330–200 and –300 series airplanes; Model A330–223F and –243F airplanes; and Model A340–200, –300, –500, and –600 series airplanes. This proposed AD was prompted by a report that during the evaluation of specific engine failure cases at take-off on Airbus flight simulators. It has been shown that with flight control primary computer (FCPC)1 inoperative, in worst case scenario, when FCPC2 and FCPC3 resets occur during rotation at take off, a transient loss of elevator control associated with a temporary incorrect flight control law reconfiguration could occur. This proposed AD would require revising the Limitations section of the applicable airplane flight manual. We are proposing this AD to prevent movement of the elevators to zero position, which could result in inducing a pitch down movement instead of a pitch up movement needed for lift off, resulting in loss of controllability of the airplane. DATES: We must receive comments on this proposed AD by February 6, 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. SUMMARY: (k) Other FAA AD Provisions BILLING CODE 4910–13–P Federal Aviation Administration Examining the AD Docket You may examine the AD docket on the Internet at https:// E:\FR\FM\22DEP1.SGM 22DEP1 Federal Register / Vol. 76, No. 246 / Thursday, December 22, 2011 / Proposed Rules 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–2011–1323; Directorate Identifier 2010–NM–212–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. jlentini on DSK4TPTVN1PROD with PROPOSALS 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 2010–0109, dated June 28, 2010 (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: On A330/A340 aeroplanes, the Flight Control Primary Computer 2 (FCPC2) and FCPC3 are supplied with power from the 2PP bus bar. Electrical transients on the 2PP bus bar occur, in particular during engine n.2 failure on A330 aeroplanes or engine n.3 failure on A340 aeroplanes. Such electrical transients lead to a FCPC2 reset. FCPC3 reset does not occur thanks to the introduction of second electrical power supply to FCPC3 from 1PP bus bar associated to the Electrical Contactor Management Unit (ECMU) standard 5. During the evaluation of specific engine failure cases at take-off on Airbus flight simulators, it has been evidenced that with VerDate Mar<15>2010 19:15 Dec 21, 2011 Jkt 226001 FCPC1 inoperative, in the worst case, when FCPC2 and FCPC3 resets occur during rotation at take off, a transient loss of elevator control associated with a temporary incorrect flight control law reconfiguration could occur. This condition leads to a movement of the elevators to the zero position, which induces a pitch down movement instead of a pitch up movement needed to lift off. In addition, it leads to a limitation of the pilot control on pitch axis and limits the pilot capacity to counter the pitch down movement during this flight phase, which constitutes an unsafe condition. To prevent such condition, [EASA] Emergency Airworthiness Directive (EAD) 2008–0010–E was issued to prohibit aeroplanes dispatch with FCPC1 inoperative (from GO to NO–GO) for certain aeroplane configurations. For other configurations, dispatch is allowed when the integrity of the FCPC3 second electrical power supply is ensured. EASA AD 2008–0010R1 was issued to: —For A340–500/–600, alleviate the dispatch restriction on aeroplanes fitted with new FCPC Standard W11 (part number (P/N) LA2K2B100GA0000) and —For A330 and A340–200/–300, to take into account the possibility to embody in service a new FCPC3 second electrical power supply equivalent to the production one. This [EASA] AD, which supersedes EASA AD 2008–0010R1 retaining its requirements, is issued to extend the applicability to the newly certified models A330–223F and A330–243F. The FAA did not issue corresponding ADs for EASA Airworthiness Directive 2008–0010–E and EASA Airworthiness Directive 2008–0010R1 since it was determined at that time that the FAA Master Minimum Equipment List (MMEL) was an acceptable method for controlling exposure of the U.S. fleet to the safety issue addressed in the EASA ADs. Since that decision was made, the FAA determined that an AD is needed to control dispatch restrictions. In addition, EASA Airworthiness Directive 2010–0109 added two new Airbus models in the applicability and we are proceeding with this FAA AD in order to address the identified unsafe condition for the U.S. fleet. You may obtain further information by examining the MCAI in the AD docket. 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 PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 79561 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 55 products of U.S. registry. We also estimate that it would take about 1 work-hour 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 $4,675, or $85 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 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. For the reasons discussed above, I certify 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. E:\FR\FM\22DEP1.SGM 22DEP1 79562 Federal Register / Vol. 76, No. 246 / Thursday, December 22, 2011 / Proposed Rules 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. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: Airbus: Docket No. FAA–2011–1323; Directorate Identifier 2010–NM–212–AD. (a) Comments Due Date We must receive comments by February 6, 2012. (b) Affected ADs None. (c) Applicability This AD applies to Airbus Model A330– 201, –202, –203, –223, –223F, –243, –243F, –301, –302, –303, –321, –322, –323, –341, –342, and –343 airplanes; and Model A340– 211, –212, –213, –311, –312, –313, –541, and –642 airplanes; certificated in any category; all serial numbers. (d) Subject Air Transport Association (ATA) of America Code 27: Flight Controls. jlentini on DSK4TPTVN1PROD with PROPOSALS (e) Reason This AD was prompted by a report that during the evaluation of specific engine failure cases at take-off on Airbus flight simulators. It has been shown that with flight control primary computer (FCPC)1 inoperative, in worst case scenario, when FCPC2 and FCPC3 resets occur during rotation at take off, a transient loss of elevator control associated with a temporary incorrect flight control law reconfiguration could occur. We are issuing this AD to prevent movement of the elevators to zero position, which could result in inducing a pitch down movement instead of a pitch up movement needed for lift off, resulting in loss of controllability 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) Airplane Flight Manual (AFM) Revision for Certain Airplanes For airplanes identified in paragraph (c) of this AD, except for airplanes identified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD: Within 30 days after the effective date of this VerDate Mar<15>2010 19:15 Dec 21, 2011 Jkt 226001 AD, revise the Limitations section of the applicable AFM to include the following statement. This may be done by inserting a copy of this AD into the AFM. ‘‘Dispatch with the FCPC ‘‘PRIM 1’’ inoperative is prohibited.’’ (1) Model A330–223F and –243F airplanes. (2) Model A330–200 and –300 series airplanes, and Model A340–200 and –300 series airplanes, on which Airbus modification 44385 has been embodied either in production or in service by Airbus Service Bulletin A330–27–3159 or Airbus Service Bulletin A340–27–4158; and on which Airbus modification 44431 has been embodied either in production or in service by Airbus Service Bulletin A330–24–3011 or Airbus Service Bulletin A340–24–4019. (3) Model A340–500 and –600 series airplanes on which Airbus modification 57698 has been embodied either in production or in service by Airbus Service Bulletin A340–27–5046. Note 1: When a statement identical to that in paragraph (g) of this AD has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM. Note 2: This dispatch restriction applies notably to Model A330–200 and –300 series airplanes, and Model A340–200 and –300 series airplanes, which have embodied Airbus Service Bulletin A330–27–3040 or Airbus Service Bulletin A340–27–4046 in service. (h) AFM Revision for Certain Other Airplanes For Model A330–200 and –300 series airplanes, and Model A340–200 and –300 series airplanes, on which Airbus modification 44385 has been embodied either in production or in service by Airbus Service Bulletin A330–27–3159 or Airbus Service Bulletin A340–27–4158; and Airbus modification 44431 has been embodied either in production or in service by Airbus Service Bulletin A330–24–3011 or Airbus Service Bulletin A340–24–4019: Within 30 days after the effective date of this AD, revise the Limitations section of the applicable AFM to include the following statement. This may be done by inserting a copy of this AD into the AFM. ‘‘Dispatch with the FCPC ‘‘PRIM 1’’ inoperative is allowed provided that the operational test of the FCPC3 second electrical power supply is successfully performed, in accordance with the instructions of Airbus AOT A330–27A3158, or AOT A340–27A4157, as applicable, before the first flight of the MMEL interval. If the test is not successful, repair in accordance with the instructions of Airbus AOT A330–27A3158 or AOT A340–27A4157, as applicable, before dispatch with FCPC ‘‘PRIM 1’’ inoperative.’’ Note 3: Model A330–223F and –243F airplanes are not affected by paragraph (h) of this AD. Note 4: When a statement identical to that in paragraph (h) of this AD has been included in the general revisions of the AFM, the general revisions may be inserted into the PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 AFM, and the copy of this AD may be removed from the AFM. (i) AFM Revision for Model A330–223F and A330–243F Airplanes For Model A330–223F and A330–243F airplanes: Within 30 days after the effective date of this AD, revise the Limitations section of the AFM to include the following statement. This may be done by inserting a copy of this AD into the AFM. ‘‘Dispatch with the FCPC ‘‘PRIM 1’’ inoperative is allowed provided that the operational test of the FCPC3 second electrical power supply is successfully performed in accordance with the instructions of Airbus AOT A330–27A3158, before the first flight of the MMEL interval. If the test is not successful, repair in accordance with the instructions of Airbus AOT A330–27A3158, before dispatch with FCPC ‘‘PRIM 1’’ inoperative.’’ Note 5: When a statement identical to that in paragraph (i) of this AD has been included in the general revisions of the AFM, the general revisions may be inserted into the AFM, and the copy of this AD may be removed from the AFM. (j) Other FAA AD Provisions The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, 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: 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. 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. (k) Related Information Refer to MCAI European Aviation Safety Agency Airworthiness Directive 2010–0109, dated June 28, 2010, for related information. E:\FR\FM\22DEP1.SGM 22DEP1 Federal Register / Vol. 76, No. 246 / Thursday, December 22, 2011 / Proposed Rules Issued in Renton, Washington, on December 14, 2011. Michael Kaszycki, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2011–32845 Filed 12–21–11; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2011–1192; Airspace Docket No. 11–ANM–22] Proposed Amendment of Class E Airspace; Sheridan, WY Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: This action proposes to amend Class E airspace at Sheridan County Airport, Sheridan, WY. Decommissioning of the Sheridan Tactical Air Navigation System (TACAN) has made this action necessary for the safety and management of Instrument Flight Rules (IFR) operations at the airport. DATES: Comments must be received on or before February 6, 2012. ADDRESSES: Send comments on this proposal to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590; telephone (202) 366–9826. You must identify FAA Docket No. FAA–2011– 1192; Airspace Docket No. 11–ANM–22, at the beginning of your comments. You may also submit comments through the Internet at https://www.regulations.gov. FOR FURTHER INFORMATION CONTACT: Eldon Taylor, Federal Aviation Administration, Operations Support Group, Western Service Center, 1601 Lind Avenue SW., Renton, WA 98057; telephone (425) 203–4537. SUPPLEMENTARY INFORMATION: SUMMARY: jlentini on DSK4TPTVN1PROD with PROPOSALS Comments Invited Interested parties are invited to participate in this proposed rulemaking by submitting such written data, views, or arguments, as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, VerDate Mar<15>2010 19:15 Dec 21, 2011 Jkt 226001 environmental, and energy-related aspects of the proposal. Communications should identify both docket numbers (FAA Docket No. FAA 2011–1192 and Airspace Docket No. 11– ANM–22) and be submitted in triplicate to the Docket Management System (see ADDRESSES section for address and phone number). You may also submit comments through the Internet at https://www.regulations.gov. Commenters wishing the FAA to acknowledge receipt of their comments on this action must submit with those comments a self-addressed stamped postcard on which the following statement is made: ‘‘Comments to FAA Docket No. FAA–2011–1192 and Airspace Docket No. 11–ANM–22’’. The postcard will be date/time stamped and returned to the commenter. All communications received on or before the specified closing date for comments will be considered before taking action on the proposed rule. The proposal contained in this action may be changed in light of comments received. All comments submitted will be available for examination in the public docket both before and after the closing date for comments. A report summarizing each substantive public contact with FAA personnel concerned with this rulemaking will be filed in the docket. Availability of NPRMs An electronic copy of this document may be downloaded through the Internet at https://www.regulations.gov. Recently published rulemaking documents can also be accessed through the FAA’s Web page at https:// www.faa.gov/airports_air_traffic/ air_traffic/publications/ airspace_amendments/. You may review the public docket containing the proposal, any comments received, and any final disposition in person in the Dockets Office (see the ADDRESSES section for the address and phone number) between 9 a.m. and 5 p.m., Monday through Friday, except federal holidays. An informal docket may also be examined during normal business hours at the Northwest Mountain Regional Office of the Federal Aviation Administration, Air Traffic Organization, Western Service Center, Operations Support Group, 1601 Lind Avenue SW., Renton, WA 98057. Persons interested in being placed on a mailing list for future NPRMs should contact the FAA’s Office of Rulemaking, (202) 267–9677, for a copy of Advisory Circular No. 11–2A, Notice of Proposed Rulemaking Distribution System, which describes the application procedure. PO 00000 Frm 00016 Fmt 4702 Sfmt 4702 79563 The Proposal The FAA is proposing an amendment to Title 14 Code of Federal Regulations (14 CFR) Part 71 by amending Class E surface airspace at Sheridan County Airport, Sheridan, WY. Airspace reconfiguration is necessary due to the decommissioning of the Sheridan TACAN. Controlled airspace is necessary for the safety and management of IFR operations at the airport. Class E airspace designations are published in paragraph 6002, of FAA Order 7400.9V, dated August 9, 2011, and effective September 15, 2011, which is incorporated by reference in 14 CFR Part 71.1. The Class E airspace designation listed in this document will be published subsequently in this Order. The FAA has determined this proposed regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them operationally current. Therefore, this proposed regulation; (1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866; (2) is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034; February 26, 1979); and (3) does not warrant preparation of a regulatory evaluation as the anticipated impact is so minimal. Since this is a routine matter that will only affect air traffic procedures and air navigation, it is certified this proposed rule, when promulgated, would not have a significant economic impact on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. The FAA’s authority to issue rules regarding aviation safety is found in Title 49 of the U.S. Code. Subtitle 1, Section 106, describes the authority for the FAA Administrator. Subtitle VII, Aviation Programs, describes in more detail the scope of the agency’s authority. This rulemaking is promulgated under the authority described in Subtitle VII, Part A, Subpart I, Section 40103. Under that section, the FAA is charged with prescribing regulations to assign the use of the airspace necessary to ensure the safety of aircraft and the efficient use of airspace. This regulation is within the scope of that authority as it would amend this proposal for controlled airspace at Sheridan County Airport, Sheridan, WY. List of Subjects in 14 CFR Part 71 Airspace, Incorporation by reference, Navigation (air). E:\FR\FM\22DEP1.SGM 22DEP1

Agencies

[Federal Register Volume 76, Number 246 (Thursday, December 22, 2011)]
[Proposed Rules]
[Pages 79560-79563]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-32845]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1323; Directorate Identifier 2010-NM-212-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 
Model A330-200 and -300 series airplanes; Model A330-223F and -243F 
airplanes; and Model A340-200, -300, -500, and -600 series airplanes. 
This proposed AD was prompted by a report that during the evaluation of 
specific engine failure cases at take-off on Airbus flight simulators. 
It has been shown that with flight control primary computer (FCPC)1 
inoperative, in worst case scenario, when FCPC2 and FCPC3 resets occur 
during rotation at take off, a transient loss of elevator control 
associated with a temporary incorrect flight control law 
reconfiguration could occur. This proposed AD would require revising 
the Limitations section of the applicable airplane flight manual. We 
are proposing this AD to prevent movement of the elevators to zero 
position, which could result in inducing a pitch down movement instead 
of a pitch up movement needed for lift off, resulting in loss of 
controllability of the airplane.

DATES: We must receive comments on this proposed AD by February 6, 
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.

Examining the AD Docket

    You may examine the AD docket on the Internet at https://

[[Page 79561]]

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-2011-1323; 
Directorate Identifier 2010-NM-212-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 2010-0109, dated June 28, 2010 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    On A330/A340 aeroplanes, the Flight Control Primary Computer 2 
(FCPC2) and FCPC3 are supplied with power from the 2PP bus bar. 
Electrical transients on the 2PP bus bar occur, in particular during 
engine n.2 failure on A330 aeroplanes or engine n.3 failure on A340 
aeroplanes. Such electrical transients lead to a FCPC2 reset. FCPC3 
reset does not occur thanks to the introduction of second electrical 
power supply to FCPC3 from 1PP bus bar associated to the Electrical 
Contactor Management Unit (ECMU) standard 5.
    During the evaluation of specific engine failure cases at take-
off on Airbus flight simulators, it has been evidenced that with 
FCPC1 inoperative, in the worst case, when FCPC2 and FCPC3 resets 
occur during rotation at take off, a transient loss of elevator 
control associated with a temporary incorrect flight control law 
reconfiguration could occur. This condition leads to a movement of 
the elevators to the zero position, which induces a pitch down 
movement instead of a pitch up movement needed to lift off. In 
addition, it leads to a limitation of the pilot control on pitch 
axis and limits the pilot capacity to counter the pitch down 
movement during this flight phase, which constitutes an unsafe 
condition.
    To prevent such condition, [EASA] Emergency Airworthiness 
Directive (EAD) 2008-0010-E was issued to prohibit aeroplanes 
dispatch with FCPC1 inoperative (from GO to NO-GO) for certain 
aeroplane configurations. For other configurations, dispatch is 
allowed when the integrity of the FCPC3 second electrical power 
supply is ensured.
    EASA AD 2008-0010R1 was issued to:

--For A340-500/-600, alleviate the dispatch restriction on 
aeroplanes fitted with new FCPC Standard W11 (part number (P/N) 
LA2K2B100GA0000)
and
--For A330 and A340-200/-300, to take into account the possibility 
to embody in service a new FCPC3 second electrical power supply 
equivalent to the production one.

    This [EASA] AD, which supersedes EASA AD 2008-0010R1 retaining 
its requirements, is issued to extend the applicability to the newly 
certified models A330-223F and A330-243F.

    The FAA did not issue corresponding ADs for EASA Airworthiness 
Directive 2008-0010-E and EASA Airworthiness Directive 2008-0010R1 
since it was determined at that time that the FAA Master Minimum 
Equipment List (MMEL) was an acceptable method for controlling exposure 
of the U.S. fleet to the safety issue addressed in the EASA ADs. Since 
that decision was made, the FAA determined that an AD is needed to 
control dispatch restrictions. In addition, EASA Airworthiness 
Directive 2010-0109 added two new Airbus models in the applicability 
and we are proceeding with this FAA AD in order to address the 
identified unsafe condition for the U.S. fleet. You may obtain further 
information by examining the MCAI in the AD docket.

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 55 products of U.S. registry. We also estimate that 
it would take about 1 work-hour 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 $4,675, or $85 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 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.
    For the reasons discussed above, I certify 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.

[[Page 79562]]

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-2011-1323; Directorate Identifier 2010-NM-
212-AD.

(a) Comments Due Date

    We must receive comments by February 6, 2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus Model A330-201, -202, -203, -223, -
223F, -243, -243F, -301, -302, -303, -321, -322, -323, -341, -342, 
and -343 airplanes; and Model A340-211, -212, -213, -311, -312, -
313, -541, and -642 airplanes; certificated in any category; all 
serial numbers.

(d) Subject

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

(e) Reason

    This AD was prompted by a report that during the evaluation of 
specific engine failure cases at take-off on Airbus flight 
simulators. It has been shown that with flight control primary 
computer (FCPC)1 inoperative, in worst case scenario, when FCPC2 and 
FCPC3 resets occur during rotation at take off, a transient loss of 
elevator control associated with a temporary incorrect flight 
control law reconfiguration could occur. We are issuing this AD to 
prevent movement of the elevators to zero position, which could 
result in inducing a pitch down movement instead of a pitch up 
movement needed for lift off, resulting in loss of controllability 
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) Airplane Flight Manual (AFM) Revision for Certain Airplanes

    For airplanes identified in paragraph (c) of this AD, except for 
airplanes identified in paragraphs (g)(1), (g)(2), and (g)(3) of 
this AD: Within 30 days after the effective date of this AD, revise 
the Limitations section of the applicable AFM to include the 
following statement. This may be done by inserting a copy of this AD 
into the AFM.
    ``Dispatch with the FCPC ``PRIM 1'' inoperative is prohibited.''
    (1) Model A330-223F and -243F airplanes.
    (2) Model A330-200 and -300 series airplanes, and Model A340-200 
and -300 series airplanes, on which Airbus modification 44385 has 
been embodied either in production or in service by Airbus Service 
Bulletin A330-27-3159 or Airbus Service Bulletin A340-27-4158; and 
on which Airbus modification 44431 has been embodied either in 
production or in service by Airbus Service Bulletin A330-24-3011 or 
Airbus Service Bulletin A340-24-4019.
    (3) Model A340-500 and -600 series airplanes on which Airbus 
modification 57698 has been embodied either in production or in 
service by Airbus Service Bulletin A340-27-5046.

    Note 1:  When a statement identical to that in paragraph (g) of 
this AD has been included in the general revisions of the AFM, the 
general revisions may be inserted into the AFM, and the copy of this 
AD may be removed from the AFM.


    Note 2: This dispatch restriction applies notably to Model A330-
200 and -300 series airplanes, and Model A340-200 and -300 series 
airplanes, which have embodied Airbus Service Bulletin A330-27-3040 
or Airbus Service Bulletin A340-27-4046 in service.

(h) AFM Revision for Certain Other Airplanes

    For Model A330-200 and -300 series airplanes, and Model A340-200 
and -300 series airplanes, on which Airbus modification 44385 has 
been embodied either in production or in service by Airbus Service 
Bulletin A330-27-3159 or Airbus Service Bulletin A340-27-4158; and 
Airbus modification 44431 has been embodied either in production or 
in service by Airbus Service Bulletin A330-24-3011 or Airbus Service 
Bulletin A340-24-4019: Within 30 days after the effective date of 
this AD, revise the Limitations section of the applicable AFM to 
include the following statement. This may be done by inserting a 
copy of this AD into the AFM.

    ``Dispatch with the FCPC ``PRIM 1'' inoperative is allowed 
provided that the operational test of the FCPC3 second electrical 
power supply is successfully performed, in accordance with the 
instructions of Airbus AOT A330-27A3158, or AOT A340-27A4157, as 
applicable, before the first flight of the MMEL interval.
    If the test is not successful, repair in accordance with the 
instructions of Airbus AOT A330-27A3158 or AOT A340-27A4157, as 
applicable, before dispatch with FCPC ``PRIM 1'' inoperative.''

    Note 3:  Model A330-223F and -243F airplanes are not affected by 
paragraph (h) of this AD.


    Note 4: When a statement identical to that in paragraph (h) of 
this AD has been included in the general revisions of the AFM, the 
general revisions may be inserted into the AFM, and the copy of this 
AD may be removed from the AFM.

(i) AFM Revision for Model A330-223F and A330-243F Airplanes

    For Model A330-223F and A330-243F airplanes: Within 30 days 
after the effective date of this AD, revise the Limitations section 
of the AFM to include the following statement. This may be done by 
inserting a copy of this AD into the AFM.

    ``Dispatch with the FCPC ``PRIM 1'' inoperative is allowed 
provided that the operational test of the FCPC3 second electrical 
power supply is successfully performed in accordance with the 
instructions of Airbus AOT A330-27A3158, before the first flight of 
the MMEL interval.
    If the test is not successful, repair in accordance with the 
instructions of Airbus AOT A330-27A3158, before dispatch with FCPC 
``PRIM 1'' inoperative.''

    Note 5: When a statement identical to that in paragraph (i) of 
this AD has been included in the general revisions of the AFM, the 
general revisions may be inserted into the AFM, and the copy of this 
AD may be removed from the AFM.

(j) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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: 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. 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.

(k) Related Information

    Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2010-0109, dated June 28, 2010, for related information.


[[Page 79563]]


    Issued in Renton, Washington, on December 14, 2011.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-32845 Filed 12-21-11; 8:45 am]
BILLING CODE 4910-13-P
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