Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes (Collectively Called A300-600 Series Airplanes), 441-444 [2010-32995]

Download as PDF 441 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations using the procedures found in 14 CFR 39.19. Send information to ATTN: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards 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 FAAapproved 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. Related Information (i) Refer to MCAI Brazilian Airworthiness Directives 2007–08–01, effective September 27, 2007, and 2009–08–03, effective August 20, 2009; Sections A2.5.2, Fuel System Limitation Items, and A2.4, Critical Design Configuration Control Limitation (CDCCL), of Appendix 2 of EMBRAER Legacy BJ— Maintenance Planning Guide MPG–1483, Revision 5, dated March 22, 2007; and the Parker CMMs listed in table 2 of this AD; for related information. Material Incorporated by Reference (j) You must use the applicable service information contained in table 3 of this AD to do the actions required by this AD, unless the AD specifies otherwise. TABLE 3—ALL MATERIAL INCORPORATED BY REFERENCE Document Revision Parker Component Maintenance Manual With Illustrated Parts List 28–41–69 ............................. Parker Component Maintenance Manual With Illustrated Parts List 28–41–66 ............................. Parker Component Maintenance Manual With Illustrated Parts List 28-41-90 ............................... Sections A2.5.2, Fuel System Limitation Items, and A2.4, Critical Design Configuration Control Limitation (CDCCL), of Appendix 2 of EMBRAER Legacy BJ—Maintenance Planning Guide MPG–1483. 2 ................................ 1 ................................ Original ...................... 5 ................................ (Parker Component Maintenance Manual With Illustrated Parts List 28–41–69, Revision 2, dated March 13, 2009, contains the service information contained in table 4 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51. an incorrect date on page 105; the correct date is March 13, 2009.) (1) The Director of the Federal Register approved the incorporation by reference of Date March 13, 2009. March 13, 2009. April 3, 2009. March 22, 2007. TABLE 4—NEW MATERIAL INCORPORATED BY REFERENCE Revision Parker Component Maintenance Manual With Illustrated Parts List 28–41–69 ............................. Parker Component Maintenance Manual With Illustrated Parts List 28–41–66 ............................. Parker Component Maintenance Manual With Illustrated Parts List 28-41-90 ............................... WReier-Aviles on DSKGBLS3C1PROD with RULES Document 2 ................................ 1 ................................ Original ...................... (2) The Director of the Federal Register previously approved the incorporation by reference of Sections A2.5.2, Fuel System Limitation Items, and A2.4, Critical Design Configuration Control Limitation (CDCCL), of Appendix 2 of EMBRAER Legacy BJ— Maintenance Planning Guide MPG–1483, Revision 5, dated March 22, 2007, on July 30, 2008 (73 FR 35908, June 25, 2008). (3) For EMBRAER service information identified in this AD, contact Empresa Brasileira de Aeronautica S.A. (EMBRAER), Technical Publications Section (PC 060), Av. Brigadeiro Faria Lima, 2170—Putim—12227– ˜ 901 Sao Jose dos Campos—SP—BRASIL; telephone +55 12 3927–5852 or +55 12 3309– 0732; fax +55 12 3927–7546; e-mail distrib@ embraer.com.br; Internet: https:// www.flyembraer.com. For Parker service information identified in this AD, contact Parker Hannifin Corporation, Aerospace Group, Electronic Systems Division, 300 Marcus Boulevard, Smithtown, New York 11787; telephone 631–231–3737; e-mail csoengineering@parker.com; Internet https:// www.parker.com. VerDate Mar<15>2010 15:20 Jan 04, 2011 Jkt 223001 (4) 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. (5) 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 https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. Issued in Renton, Washington, on December 17, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–32998 Filed 1–4–11; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00023 Fmt 4700 Sfmt 4700 Date March 13, 2009. March 13, 2009. April 3, 2009. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–1278; Directorate Identifier 2010–NM–260–AD; Amendment 39–16567; AD 2011–01–13] RIN 2120–AA64 Airworthiness Directives; Airbus Model A300 B4–600, B4–600R, and F4–600R Series Airplanes, and Model C4–605R Variant F Airplanes (Collectively Called A300–600 Series Airplanes) Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule; request for comments. AGENCY: E:\FR\FM\05JAR1.SGM 05JAR1 442 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 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: During a routine maintenance check on an A300–600 aeroplane, the operator found the pitch uncoupling unit installed at an incorrect location. The pitch uncoupling unit was inverted with the rod assembly. After a complete inspection of all A300– 600 aeroplanes of its fleet, the operator identified the same incorrect installation on another aeroplane. * * * * * This condition, if not detected and corrected, in combination with particular failure modes, could lead to loss of control of the aeroplane during the takeoff phase. WReier-Aviles on DSKGBLS3C1PROD with RULES * * * * * This AD requires actions that are intended to address the unsafe condition described in the MCAI. DATES: This AD becomes effective January 20, 2011. The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of January 20, 2011. We must receive comments on this AD by February 22, 2011. 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 W12–40, 1200 New Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. Examining the AD Docket You may examine the AD docket on the Internet at 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 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. VerDate Mar<15>2010 15:20 Jan 04, 2011 Jkt 223001 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. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: Discussion The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA Emergency Airworthiness Directive 2010–0239–E, dated November 19, 2010 [Corrected November 23, 2010] (referred to after this as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: During a routine maintenance check on an A300–600 aeroplane, the operator found the pitch uncoupling unit installed at an incorrect location. The pitch uncoupling unit was inverted with the rod assembly. After a complete inspection of all A300– 600 aeroplanes of its fleet, the operator identified the same incorrect installation on another aeroplane. Had this routine maintenance check, which was accomplished for other purposes, not been carried out, the incorrect installation could only have been detected during the accomplishment of the pitch uncoupling functional test. Note: Another maintenance task, the pitch uncoupling operational test, scheduled at intervals not to exceed 2,000 FH or 36 months, whichever occurs first (MPD task 273100–01–1), only validates the condition of the pitch uncoupling solenoid. This condition, if not detected and corrected, in combination with particular failure modes, could lead to loss of control of the aeroplane during the takeoff phase. For the reason described above, this AD requires a one time visual inspection, to detect any incorrect installation of the pitch uncoupling unit,and, depending on findings, to take corrective actions. This [EASA] AD was republished to correct the compliance time. Corrective actions include removing and re-installing the pitch uncoupling unit and rod assembly at the correction location and doing a functional test to verify correct operation. You may obtain further information by examining the MCAI in the AD docket. Relevant Service Information Airbus has issued A300–600 All Operators Telex 27A6068, Revision 01, dated November 18, 2010. The actions described in this service information are intended to correct the unsafe condition identified in the MCAI. PO 00000 Frm 00024 Fmt 4700 Sfmt 4700 FAA’s Determination and Requirements of This 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 issuing this AD because we evaluated all pertinent information and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. Differences Between the 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 FAA policies. Any such differences are highlighted in a Note within the AD. FAA’s Determination of the Effective Date An unsafe condition exists that requires the immediate adoption of this AD. The FAA has found that the risk to the flying public justifies waiving notice and comment prior to adoption of this rule because a pitch uncoupling unit was found to be installed at an incorrect location. The pitch uncoupling unit was inverted with the rod assembly. This condition, if not detected and corrected, in combination with other failure modes, could lead to loss of control of the airplane during the take-off phase. Therefore, we determined that notice and opportunity for public comment before issuing this AD are impracticable and that good cause exists for making this amendment effective in fewer than 30 days. Comments Invited This AD is a final rule that involves requirements affecting flight safety, and we did not precede it by notice and opportunity for public comment. We invite you to send any written relevant data, views, or arguments about this AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2010–1278; Directorate Identifier 2010–NM–260– E:\FR\FM\05JAR1.SGM 05JAR1 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this AD. We will consider all comments received by the closing date and may amend this AD because of 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 AD. 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. WReier-Aviles on DSKGBLS3C1PROD with RULES 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. VerDate Mar<15>2010 15:20 Jan 04, 2011 Jkt 223001 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: ■ 2011–01–13 Airbus: Amendment 39–16567. Docket No. FAA–2010–1278; Directorate Identifier 2010–NM–260–AD. Effective Date (a) This airworthiness directive (AD) becomes effective January 20, 2011. Affected ADs (b) None. Applicability (c) 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, certificated in any category, all serial numbers, except for airplanes on which the pitch uncoupling functional test has already been performed in service since new. Note 1: The pitch uncoupling functional test is described in Section 3.D.(2) of task 27– 31–00, Page Block 501 of Airbus A300–600 Aircraft Maintenance Manual (AMM) [Maintenance Planning Document (MPD) task 273100–02–1]. Subject (d) Air Transport Association (ATA) of America Code 27: Flight Controls. Reason (e) The mandatory continued airworthiness information (MCAI) states: During a routine maintenance check on an A300–600 aeroplane, the operator found the pitch uncoupling unit installed at an incorrect location. The pitch uncoupling unit was inverted with the rod assembly. After a complete inspection of all A300– 600 aeroplanes of its fleet, the operator identified the same incorrect installation on another aeroplane. * * * * * This condition, if not detected and corrected, in combination with particular failure modes, could lead to loss of control of the aeroplane during the takeoff phase. * PO 00000 * * Frm 00025 * Fmt 4700 * Sfmt 4700 443 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, Re-Installation, and Functional Test (g) Within 30 days after the effective date of this AD, do a general visual inspection for correct location of the pitch uncoupling unit, in accordance with paragraph 4.2 of Airbus A300–600 All Operators Telex (AOT) 27A6068, Revision 01, dated November 18, 2010. If the pitch uncoupling unit is found inverted with the rod assembly, before further flight, remove and re-install the uncoupling unit and the rod assembly at their correct locations and do a functional test of the pitch uncoupling unit to verify correct operation, in accordance with paragraph 4.2 of Airbus A300–600 AOT 27A6068, Revision 01, dated November 18, 2010. FAA AD Differences Note 2: This AD differs from the MCAI and/or service information as follows: No differences. Other FAA AD Provisions (h) The following provisions also apply to this AD: (1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–2125; fax (425) 227–1149. Information may be e-mailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards 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 FAAapproved 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 E:\FR\FM\05JAR1.SGM 05JAR1 444 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 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. Related Information (i) Refer to MCAI European Aviation Safety Agency Emergency Airworthiness Directive 2010–0239–E, dated November 19, 2010 [Corrected November 23, 2010]; and Airbus A300–600 AOT 27A6068, Revision 01, dated November 18, 2010; for related information. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2010–1023 Directorate Identifier 2010–CE–055–AD; Amendment 39–16557; AD 2011–01–04] RIN 2120–AA64 Airworthiness Directives; Empresa Brasileira de Aeronautica S.A. (EMBRAER) Model EMB–500 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) issued 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: fax: ++55 12 3927–2610; E-mail: reliability.executive@embraer.com.br; Internet: https://www.embraer.com.br. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call 816–329– 4148. FOR FURTHER INFORMATION CONTACT: Jim Rutherford, Aerospace Engineer, FAA, Small Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri 64106; telephone: (816) 329–4165; fax: (816) 329–4090. SUPPLEMENTARY INFORMATION: Discussion Material Incorporated by Reference SUMMARY: (j) You must use Airbus A300–600 All Operators Telex 27A6068, Revision 01, dated November 18, 2010, 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 https:// 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: https://www.archives.gov/federal_register/ code_of_federal_regulations/ ibr_locations.html. 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 October 15, 2010 (75 FR 63422). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: It has been detected a short circuit in harness W101 due to its interference with the main door mechanism. Further analysis of the affected region has also revealed the possibility of chafing between the same harness and the oxygen tubing. The chafing of the wiring harness against the oxygen tubing could lead to a short circuit of the wiring harness and a subsequent fire in the airplane. Since this condition may occur in other airplanes of the same type and affects flight safety, a corrective action is required. Thus, sufficient reason exists to request compliance with this AD in the indicated time limit. It has been detected a short circuit in harness W101 due to its interference with the main door mechanism. Further analysis of the affected region has also revealed the possibility of chafing between the same harness and the oxygen tubing. The chafing of the wiring harness against the oxygen tubing could lead to a short circuit of the wiring harness and a subsequent fire in the airplane. Since this condition may occur in other airplanes of the same type and affects flight safety, a corrective action is required. Thus, sufficient reason exists to request compliance with this AD in the indicated time limit. We are issuing this AD to require actions to correct the unsafe condition on these products. DATES: This AD becomes effective February 9, 2011. On February 9, 2011, the Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at Document Management Facility, U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590. For service information identified in this AD, contact EMBRAER Empresa ´ Brasileira de Aeronautica S.A., Phenom Maintenance Support, Av. Brig. Farina Lima, 2170, Sao Jose dos Campos—SP, CEP: 12227–901—PO Box: 38/2, BRASIL, telephone: ++55 12 3927–5383; The MCAI requires installing clamps to the W101 wiring harness. Issued in Renton, Washington, on December 22, 2010. Jeffrey E. Duven, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2010–32995 Filed 1–4–11; 8:45 am] WReier-Aviles on DSKGBLS3C1PROD with RULES BILLING CODE 4910–13–P VerDate Mar<15>2010 15:20 Jan 04, 2011 Jkt 223001 PO 00000 Frm 00026 Fmt 4700 Sfmt 4700 Comments We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Conclusion We reviewed the available data 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 E:\FR\FM\05JAR1.SGM 05JAR1

Agencies

[Federal Register Volume 76, Number 3 (Wednesday, January 5, 2011)]
[Rules and Regulations]
[Pages 441-444]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-32995]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1278; Directorate Identifier 2010-NM-260-AD; 
Amendment 39-16567; AD 2011-01-13]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and 
F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes 
(Collectively Called A300-600 Series Airplanes)

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule; request for comments.

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

[[Page 442]]

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:

    During a routine maintenance check on an A300-600 aeroplane, the 
operator found the pitch uncoupling unit installed at an incorrect 
location. The pitch uncoupling unit was inverted with the rod 
assembly.
    After a complete inspection of all A300-600 aeroplanes of its 
fleet, the operator identified the same incorrect installation on 
another aeroplane.
* * * * *
    This condition, if not detected and corrected, in combination 
with particular failure modes, could lead to loss of control of the 
aeroplane during the takeoff phase.

* * * * *
This AD requires actions that are intended to address the unsafe 
condition described in the MCAI.

DATES: This AD becomes effective January 20, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in the AD as of January 20, 
2011.
    We must receive comments on this AD by February 22, 2011.

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 W12-40, 1200 New 
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.

Examining the AD Docket

    You may examine the AD docket on the Internet at 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 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:

Discussion

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Community, has issued EASA 
Emergency Airworthiness Directive 2010-0239-E, dated November 19, 2010 
[Corrected November 23, 2010] (referred to after this as ``the MCAI''), 
to correct an unsafe condition for the specified products. The MCAI 
states:

    During a routine maintenance check on an A300-600 aeroplane, the 
operator found the pitch uncoupling unit installed at an incorrect 
location. The pitch uncoupling unit was inverted with the rod 
assembly.
    After a complete inspection of all A300-600 aeroplanes of its 
fleet, the operator identified the same incorrect installation on 
another aeroplane.
Had this routine maintenance check, which was accomplished for other 
purposes, not been carried out, the incorrect installation could 
only have been detected during the accomplishment of the pitch 
uncoupling functional test.

    Note:  Another maintenance task, the pitch uncoupling 
operational test, scheduled at intervals not to exceed 2,000 FH or 
36 months, whichever occurs first (MPD task 273100-01-1), only 
validates the condition of the pitch uncoupling solenoid.

    This condition, if not detected and corrected, in combination 
with particular failure modes, could lead to loss of control of the 
aeroplane during the takeoff phase.
    For the reason described above, this AD requires a one time 
visual inspection, to detect any incorrect installation of the pitch 
uncoupling unit,and, depending on findings, to take corrective 
actions.
    This [EASA] AD was republished to correct the compliance time.

    Corrective actions include removing and re-installing the pitch 
uncoupling unit and rod assembly at the correction location and doing a 
functional test to verify correct operation. You may obtain further 
information by examining the MCAI in the AD docket.

Relevant Service Information

    Airbus has issued A300-600 All Operators Telex 27A6068, Revision 
01, dated November 18, 2010. 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 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 issuing this AD because we 
evaluated all pertinent information and determined the unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between the 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 FAA policies. Any such differences are 
highlighted in a Note within the AD.

FAA's Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD. The FAA has found that the risk to the flying public justifies 
waiving notice and comment prior to adoption of this rule because a 
pitch uncoupling unit was found to be installed at an incorrect 
location. The pitch uncoupling unit was inverted with the rod assembly. 
This condition, if not detected and corrected, in combination with 
other failure modes, could lead to loss of control of the airplane 
during the take-off phase. Therefore, we determined that notice and 
opportunity for public comment before issuing this AD are impracticable 
and that good cause exists for making this amendment effective in fewer 
than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety, and we did not precede it by notice and opportunity for public 
comment. We invite you to send any written relevant data, views, or 
arguments about this AD. Send your comments to an address listed under 
the ADDRESSES section. Include ``Docket No. FAA-2010-1278; Directorate 
Identifier 2010-NM-260-

[[Page 443]]

AD'' at the beginning of your comments. We specifically invite comments 
on the overall regulatory, economic, environmental, and energy aspects 
of this AD. We will consider all comments received by the closing date 
and may amend this AD because of 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 AD.

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.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

0
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:

2011-01-13 Airbus: Amendment 39-16567. Docket No. FAA-2010-1278; 
Directorate Identifier 2010-NM-260-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
20, 2011.

Affected ADs

    (b) None.

Applicability

    (c) 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, certificated in any category, all serial numbers, except 
for airplanes on which the pitch uncoupling functional test has 
already been performed in service since new.

    Note 1: The pitch uncoupling functional test is described in 
Section 3.D.(2) of task 27-31-00, Page Block 501 of Airbus A300-600 
Aircraft Maintenance Manual (AMM) [Maintenance Planning Document 
(MPD) task 273100-02-1].

Subject

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

Reason

    (e) The mandatory continued airworthiness information (MCAI) 
states:
    During a routine maintenance check on an A300-600 aeroplane, the 
operator found the pitch uncoupling unit installed at an incorrect 
location. The pitch uncoupling unit was inverted with the rod 
assembly.
    After a complete inspection of all A300-600 aeroplanes of its 
fleet, the operator identified the same incorrect installation on 
another aeroplane.
* * * * *
    This condition, if not detected and corrected, in combination 
with particular failure modes, could lead to loss of control of the 
aeroplane during the takeoff phase.
* * * * *

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, Re-Installation, and Functional Test

    (g) Within 30 days after the effective date of this AD, do a 
general visual inspection for correct location of the pitch 
uncoupling unit, in accordance with paragraph 4.2 of Airbus A300-600 
All Operators Telex (AOT) 27A6068, Revision 01, dated November 18, 
2010. If the pitch uncoupling unit is found inverted with the rod 
assembly, before further flight, remove and re-install the 
uncoupling unit and the rod assembly at their correct locations and 
do a functional test of the pitch uncoupling unit to verify correct 
operation, in accordance with paragraph 4.2 of Airbus A300-600 AOT 
27A6068, Revision 01, dated November 18, 2010.

FAA AD Differences

    Note 2:  This AD differs from the MCAI and/or service 
information as follows: No differences.

Other FAA AD Provisions

    (h) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
has the authority to approve AMOCs for this AD, if requested using 
the procedures found in 14 CFR 39.19. Send information to ATTN: Dan 
Rodina, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 
98057-3356; telephone (425) 227-2125; fax (425) 227-1149. 
Information may be e-mailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC on any airplane to which the AMOC 
applies, notify your principal maintenance inspector (PMI) or 
principal avionics inspector (PAI), as appropriate, or lacking a 
principal inspector, your local Flight Standards 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

[[Page 444]]

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.

Related Information

    (i) Refer to MCAI European Aviation Safety Agency Emergency 
Airworthiness Directive 2010-0239-E, dated November 19, 2010 
[Corrected November 23, 2010]; and Airbus A300-600 AOT 27A6068, 
Revision 01, dated November 18, 2010; for related information.

Material Incorporated by Reference

    (j) You must use Airbus A300-600 All Operators Telex 27A6068, 
Revision 01, dated November 18, 2010, 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 https://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: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on December 22, 2010.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-32995 Filed 1-4-11; 8:45 am]
BILLING CODE 4910-13-P
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