Airworthiness Directives; Airbus Airplanes, 40485-40488 [2012-15897]

Download as PDF Federal Register / Vol. 77, No. 132 / Tuesday, July 10, 2012 / Rules and Regulations Note 1 to paragraph (j)(2) of this AD: For airplanes identified in paragraph (j)(2) of this AD, post-modification inspection guidance may be included in an approved alternative method of compliance (AMOC) for paragraph (j)(2) of this AD. (k) Post-Modification Inspection of the Modified Areas For airplanes identified in paragraph (j)(1) of this AD, within 20,000 flight cycles after doing the modification required by paragraph (j) of this AD: Do an inspection for cracks of the modified areas of the left- and right-side tension tie structure and frame structure, in accordance with a method approved in accordance with the procedures specified in paragraph (n) of this AD. If any crack is found during any inspection required by this paragraph, before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (n) of this AD. (l) Post-Modification Repetitive Inspections of the Unmodified Areas (1) For airplanes identified in paragraph (j)(1) of this AD, within 6,000 flight cycles after doing the modification required by paragraph (j) of this AD: Do a detailed inspection for cracks on the unmodified areas of the left- and right-side tension tie structure and frame structure, at certain stations, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2605, Revision 1, dated May 27, 2010. If any crack is found during any inspection required by this paragraph, before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (n) of this AD. Repeat the inspection of the unmodified areas thereafter at intervals not to exceed 6,000 flight cycles. (2) Boeing Alert Service Bulletin 747– 53A2605, Revision 1, dated May 27, 2010, refers to Section 51–10–02 of the Boeing 747– 400F Structural Repair Manual (SRM) and Section 51–10–01 of the Boeing 747–100/ 200/300 SRM as additional sources of guidance for removing small cracks and fatigue damage material from the existing holes in the unmodified center section of the tension tie channels. Where those SRM sections state that ‘‘zero-timing must only be used where specifically permitted in an SRM chapter-section-repair,’’ this AD allows the zero-timing procedures specified in those SRM sections. wreier-aviles on DSK6TPTVN1PROD with RULES (m) Credit for Previous Actions This paragraph provides credit for the actions required by paragraphs (j), (k), and (l)(1) of this AD, if those actions were performed before the effective date of this AD using Boeing Alert Service Bulletin 747– 53A2605, dated October 8, 2009. (n) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), 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 VerDate Mar<15>2010 14:44 Jul 09, 2012 Jkt 226001 appropriate. If sending information directly to the manager of the ACO, send it to the attention of the person identified in the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. (2) 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. (3) An AMOC that provides an acceptable level of safety may be used for any repair required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO to make those findings. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Certain actions required by paragraphs (g) and (h) of this AD are approved as AMOCs for the requirements specified in paragraphs (n)(4)(i), (n)(4)(ii), and (n)(4)(iii) of this AD. All provisions of the referenced ADs specified in paragraphs (n)(4)(i), (n)(4)(ii), and (n)(4)(iii) of this AD, including applicable post-modification inspection thresholds, remain fully applicable and must be complied with. (i) Repairs or modifications of the aft tension tie channels done in accordance with this AD are AMOCs for the repair requirements of paragraph A. of AD 84–19– 01, Amendment 39–4913 (49 FR 35365, September 17, 1984); and paragraphs (a)(2) and (b)(2) of AD 94–13–06, Amendment 39– 8946 (59 FR 32879, June 27, 1994). (ii) The inspection requirements of this AD are AMOCs for the post-modification inspection requirements of paragraph B. of AD 84–19–01, Amendment 39–4913 (49 FR 35365, September 17, 1984); and paragraph (b) of AD 94–13–06, Amendment 39–8946 (59 FR 32879, June 27, 1994). (iii) The inspection requirements of this AD are AMOCs for the inspections of Structural Significant Item (SSI) F–19A of Boeing Supplemental Structural Inspection Document D6–35022, Revision G, dated December 2000, as required by paragraphs (h) and (i) of AD 2004–07–22 R1, Amendment 39–15326 (73 FR 1052, January 7, 2008); corrected February 14, 2008 (73 FR 8589). (5) AMOCs approved previously in accordance with AD 2006–01–07, Amendment 39–14446 (71 FR 1947, January 12, 2006), are approved as AMOCs for the corresponding provisions of paragraph (g) of this AD. (6) AMOCs approved previously in accordance with AD 2006–01–07, Amendment 39–14446 (71 FR 1947, January 12, 2006), are approved as AMOCs for the corresponding repairs or modifications required by paragraph (h) of this AD provided that the actions are done within the compliance times specified in paragraph (h) of this AD. Compliance times in previously approved AMOCs are not approved for paragraph (h) of this AD. (o) Related Information For more information about this AD, contact Nathan Weigand, Aerospace PO 00000 Frm 00027 Fmt 4700 Sfmt 4700 40485 Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917– 6428; fax: (425) 917–6590; email: nathan.p.weigand@faa.gov. (p) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. (3) The following service information was approved for IBR on August 14, 2012. (i) Boeing Alert Service Bulletin 747– 53A2502, Revision 1, dated June 17, 2010. (ii) Boeing Alert Service Bulletin 747– 53A2605, Revision 1, dated May 27, 2010. (4) The following service info was approved for IBR on February 16, 2006 (71 FR 1947, January 12, 2006). (i) Boeing Special Attention Service Bulletin 747–53A2502, dated April 21, 2005. (5) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax 206–766–5680; Internet https://www.myboeingfleet.com. (6) 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. (7) 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/ cfr/ibr_locations.html. Issued in Renton, Washington, on June 19, 2012. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–15894 Filed 7–9–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2012–0040; Directorate Identifier 2011–NM–121–AD; Amendment 39–17108; AD 2012–13–06] RIN 2120–AA64 Airworthiness Directives; Airbus Airplanes Federal Aviation Administration (FAA), Department of Transportation (DOT). ACTION: Final rule. AGENCY: E:\FR\FM\10JYR1.SGM 10JYR1 40486 Federal Register / Vol. 77, No. 132 / Tuesday, July 10, 2012 / Rules and Regulations We are adopting a new airworthiness directive (AD) for all Airbus Model A300 series airplanes; all Model A300 B4–600, B4–600R, and F4– 600R series airplanes, and Model 300 C4–605R Variant F airplanes (collectively called A300–600 series airplanes). This AD was prompted by reports of an inoperative fire shut-off valve (FSOV) as a result of damage due to over-length of the bonding lead. This AD requires a one-time detailed inspection for length of the FSOV bonding leads and for contact or chafing of the wires, and corrective actions, if necessary. We are issuing this AD to detect and correct contact or chafing of wires and bonding leads which, if not detected could be a source of sparks in the wing trailing edge, and could lead to an uncontrolled engine fire. DATES: This AD becomes effective August 14, 2012. The Director of the Federal Register approved the incorporation by reference of certain publications listed in this AD as of August 14, 2012. ADDRESSES: You may examine the AD docket on the Internet at https:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC. FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, Washington 98057–3356; telephone 425–227–2125; fax 425–227–1149. SUPPLEMENTARY INFORMATION: SUMMARY: wreier-aviles on DSK6TPTVN1PROD with RULES Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on February 6, 2012 (77 FR 5728). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states: During a scheduled maintenance check, one operator reported inoperative FSOV [fire shut-off valve]. Investigations showed damage at wire located between engine 2 Hydraulic FSOV and wing rear spar, in the zones 575/675, and at bonding lead, located between wing Rib 7A and Rib 8 below Hydraulic Pressure Lines. Similar inspections on different aeroplanes have shown that one of the causes of damage, is the contact between bonding lead and the harness, due to over length of the bonding lead. As the affected wire is not powered during normal operation, no defect had been VerDate Mar<15>2010 14:44 Jul 09, 2012 Jkt 226001 detected. The defect was detected when a test was performed on the FSOV during maintenance check by the operator. This condition, in the scope of published FAA SFAR88 and JAA Internal Policy INT/ POL/25/12, is considered to be a potential source of sparks in the wing trailing edge area and if not detected, could lead to an uncontrolled engine fire. For the reasons stated above, this [EASA] AD requires a one-time [detailed] inspection of the wires [for contact or chafing] located between LH/RH engines Hydraulic FSOV and wing rear spar in the zones 575/675, and the bonding lead [for length] that is located between Rib 7A and Rib 8 below Hydraulic Pressure Lines, and corrective actions [repair wires or replace bonding leads] depending on findings. You may obtain further information by examining the MCAI in the AD docket. Comments We gave the public the opportunity to participate in developing this AD. We have considered the comment received. Request To Extend the Compliance Time UPS Airlines requested that we extend the compliance time from 30 to 40 months after the effective date of the AD. The commenter stated the extension is a better fit within the operator’s heavy maintenance program because the extended compliance time is more conducive to schedule-required aircraft ground time, labor, and parts acquisition. The commenter stated that the compliance time is too restrictive. We do not agree with the commenter’s request to extend the compliance time. In developing the proposed compliance time, we determined that the compliance time of 4,500 flight hours or 30 months after the effective date of the AD, whichever occurs first, is appropriate when considering the safety implications, the average utilization rate of the affected fleet, the practical aspects of an orderly inspection of the fleet during heavy maintenance checks, and the availability of required replacement parts. In addition, our compliance time corresponds with the compliance time of the parallel AD issued by European Aviation Safety Agency (EASA). We have not changed the AD in this regard. Explanation of Change to AD We have changed paragraph (i) of this AD to include a compliance time of ‘‘before further flight’’ for the wire repair. This compliance time was required by EASA AD 2011–0084, dated May 24, 2011, and was inadvertently omitted from the NPRM (77 FR 5728, February 6, 2012). PO 00000 Frm 00028 Fmt 4700 Sfmt 4700 Conclusion We reviewed the available data, including the comment received, and determined that air safety and the public interest require adopting the AD with the change described previously— and minor editorial changes. We have determined that these minor changes: • Are consistent with the intent that was proposed in the NPRM (77 FR 5728, February 6, 2012) for correcting the unsafe condition; and • Do not add any additional burden upon the public than was already proposed in the NPRM (77 FR 5728, February 6, 2012). We also determined that these changes will not increase the economic burden on any operator or increase the scope of the AD. Costs of Compliance We estimate that this AD will affect 125 products of U.S. registry. We also estimate that it will take about 8 workhours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $85,000, or $680 per product. In addition, we estimate that any necessary follow-on actions would take about 1 work-hour and require parts costing $50, for a cost of $135 per product. We have no way of determining the number of products that may need these actions. Authority for This Rulemaking Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘Subtitle VII: Aviation Programs,’’ describes in more detail the scope of the Agency’s authority. We are issuing this rulemaking under the authority described in ‘‘Subtitle VII, Part A, Subpart III, Section 44701: General requirements.’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on E:\FR\FM\10JYR1.SGM 10JYR1 Federal Register / Vol. 77, No. 132 / Tuesday, July 10, 2012 / Rules and Regulations 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 that this AD: 1. Is not a ‘‘significant regulatory action’’ under Executive Order 12866; 2. Is not a ‘‘significant rule’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); 3. Will not affect intrastate aviation in Alaska; and 4. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act. We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. 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 the NPRM (77 FR 5728, February 6, 2012), the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: PART 39—AIRWORTHINESS DIRECTIVES 1. The authority citation for part 39 continues to read as follows: ■ Authority: 49 U.S.C. 106(g), 40113, 44701. § 39.13 [Amended] 2. The FAA amends § 39.13 by adding the following new AD: wreier-aviles on DSK6TPTVN1PROD with RULES ■ 2012–13–06 Airbus: Amendment 39–17108. Docket No. FAA–2012–0040; Directorate Identifier 2011–NM–121–AD. (a) Effective Date This airworthiness directive (AD) becomes effective August 14, 2012. (b) Affected ADs None. VerDate Mar<15>2010 14:44 Jul 09, 2012 Jkt 226001 (c) Applicability This AD applies to airplanes specified in paragraphs (c)(1), (c)(2) and (c)(3) of this AD; certificated in any category; all certificated models; all serial numbers. (1) Airbus Model A300 B2–1A, B2–1C, B2K–3C, B2–203, B4–2C, B4–103, and B4– 203 airplanes. (2) Airbus Model A300 B4–601, B4–603, B4–620, B4–622, B4–605R, B4–622R, F4– 605R, and F4–622 airplanes. (3) Airbus Model A300 C4–605R Variant F airplanes. (d) Subject Air Transport Association (ATA) of America Code 24: Electrical Power. (e) Reason This AD was prompted by reports of an inoperative fire shut-off valve (FSOV) as a result of damage due to over-length of the bonding lead. We are issuing this AD to detect and correct contact or chafing of wires and bonding leads which, if not detected, could be a source of sparks in the wing trailing edge, and could lead to an uncontrolled engine fire. (f) Compliance You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done. (g) Inspection of the FSOV Bonding Leads Within 4,500 flight hours or 30 months after the effective date of this AD, whichever occurs first: Do a one-time detailed inspection for length of the FSOV bonding leads, and for contact or chafing of the wires located on left hand (LH) side and right-hand (RH) side of the wing rear spar, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–24– 0106, dated July 9, 2010 (for Model A300 series airplanes); or Airbus Mandatory Service Bulletin A300–24–6108, dated July 9, 2010 (for Model A300–600 series airplanes). (h) Corrective Action for FSOV Bonding Leads If, during the inspection required by paragraph (g) of this AD, the length of the bonding lead(s) is more than 80 mm (3.15 inches), before further flight, replace the bonding lead(s) with a new bonding lead having a length equal to 80 mm (3.15 inches), in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–24–0106, dated July 9, 2010 (for Model A300 series airplanes); or Airbus Mandatory Service Bulletin A300–24–6108, dated July 9, 2010 (for Model A300–600 series airplanes). (i) Repair of the Wires of the LH and RH Sides If, during the inspection required by paragraph (g) of this AD, contact(s) or chafing(s) of the wires is found, repair the wires, before further flight, in accordance with the Accomplishment Instructions of Airbus Mandatory Service Bulletin A300–24– 0106, dated July 9, 2010 (for Model A300 series airplanes); or Airbus Mandatory PO 00000 Frm 00029 Fmt 4700 Sfmt 4700 40487 Service Bulletin A300–24–6108, dated July 9, 2010 (for Model A300–600 series airplanes). (j) Parts Installation Prohibition As of the effective date of this AD, no person may install any bonding lead longer than 80 mm (3.15 inches), located between LH/RH engine hydraulic FSOV and wing rear spar in the zones 575/675 on any airplane. (k) 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: 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. (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 Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2011–0084, dated May 24, 2011, and the service information identified in paragraphs (l)(1) and (l)(2) of this AD, for related information. (1) Airbus Mandatory Service Bulletin A300–24–0106, dated July 9, 2010. (2) Airbus Mandatory Service Bulletin A300–24–6108, dated July 9, 2010. (m) Material Incorporated by Reference (1) The Director of the Federal Register approved the incorporation by reference (IBR) of the following service information under 5 U.S.C. 552(a) and 1 CFR part 51. (2) You must use the following service information to do the actions required by this AD, unless the AD specifies otherwise. (i) Airbus Mandatory Service Bulletin A300–24–0106, excluding Appendix 01, and including Appendix 2, dated July 9, 2010. (ii) Airbus Mandatory Service Bulletin A300–24–6108, excluding Appendix 01 and including Appendix 2, dated July 9, 2010. (3) 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; email: account.airwortheas@airbus.com; Internet https:// www.airbus.com. (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 E:\FR\FM\10JYR1.SGM 10JYR1 40488 Federal Register / Vol. 77, No. 132 / Tuesday, July 10, 2012 / Rules and Regulations 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 an NARA facility, 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 June 21, 2012. John P. Piccola, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2012–15897 Filed 7–9–12; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 71 [Docket No. FAA–2012–0456; Airspace Docket No. 12–AEA–9] Amendment of Class D and Class E Airspace; Lakehurst, NJ Federal Aviation Administration (FAA), DOT. ACTION: Final rule, technical amendment. AGENCY: This action changes the name of the airport associated with the Class D and Class E airspace at Lakehurst, NJ. The airport’s name is being changed to Lakehurst Naval Support Activity/ Maxfield Field (Joint Base McGuire-DixLakehurst). The FAAs Aeronautical Products office requested the change to reflect the current airport name. DATES: Effective date 0901 UTC, September 20, 2012. The Director of the Federal Register approves this incorporation by reference action under Title 1, Code of Federal Regulations, part 51, subject to the annual revision of FAA Order 7400.9 and publication of conforming amendments. FOR FURTHER INFORMATION CONTACT: John Fornito, Operations Support Group, Eastern Service Center, Federal Aviation Administration, P.O. Box 20636, Atlanta, Georgia 30320; telephone (404) 305–6364. SUPPLEMENTARY INFORMATION: wreier-aviles on DSK6TPTVN1PROD with RULES SUMMARY: The Rule This amendment to Title 14, Code of Federal Regulations (14 CFR) part 71 changes the name of the airport associated with the Class D airspace and Class E airspace designated as an extension to a Class D airspace, at Lakehurst, NJ. The airport name is VerDate Mar<15>2010 14:44 Jul 09, 2012 Jkt 226001 changed from Lakehurst Naval Air Experimental Center Airport/Maxfield Field to Lakehurst Naval Support Activity/Maxfield Field (Joint Base McGuire-Dix-Lakehurst) to be in concert with the FAAs aeronautical database. Accordingly, since this is an administrative change, and does not affect the boundaries, altitudes, or operating requirements of the airspace, notice and public procedures under 5 U.S.C. 553(b) are unnecessary. The Class D airspace, and Class E airspace designations are published in Paragraph 5000 and 6004, respectively, of FAA Order 7400.9V, dated August 9, 2011, and effective September 15, 2011, which is incorporated by reference in 14 CFR 71.1. The Class D and Class E airspace designations listed in this document will be published subsequently in the Order. The FAA has determined that this regulation only involves an established body of technical regulations for which frequent and routine amendments are necessary to keep them, operationally current, is non-controversial and unlikely to result in adverse or negative comments. It, therefore, (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 that this rule, when promulgated, will 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 United States Code. 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. 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 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 amends controlled airspace for the Lakehurst, NJ, Class D and E airspace area. Lists of Subjects in 14 CFR Part 71 Airspace, Incorporation by reference, Navigation (air). PO 00000 Frm 00030 Fmt 4700 Sfmt 4700 Final Rule In consideration of the foregoing, the Federal Aviation Administration amends 14 CFR part 71 as follows: PART 71—DESIGNATION OF CLASS A, B, C, D, AND E AIRSPACE AREAS; AIR TRAFFIC SERVICE ROUTES; AND REPORTING POINTS 1. The authority citation for part 71 continues to read as follows: ■ Authority: 49 U.S.C. 106(g); 40103, 40113, 40120; E.O. 10854, 24 FR 9565, 3 CFR, 1959– 1963 Comp., p. 389. § 71.1 [Amended] 2. The incorporation by reference in 14 CFR 71.1 of Federal Aviation Administration Order 7400.9V, Airspace Designations and Reporting Points, dated August 9, 2011, effective September 15, 2011, is amended as follows: ■ Paragraph 5000 Class D airspace. * * * AEA NJ D * * Lakehurst, NJ [Amended] Lakehurst Naval Support Activity/Maxfield Field, NJ (Joint Base McGuire-DixLakehurst) (Lat. 40°02′00″ N., long. 74°21′13″ W.) That airspace extending upward from the surface to and including 2,600 feet MSL within a 4.2-mile radius of the Lakehurst Naval Support Activity/Maxfield Field (Joint Base McGuire-Dix-Lakehurst). This Class D airspace area is effective during the specific dates and times established in advance by a Notice to Airmen. The effective date and time will thereafter be continuously published in the Airport/Facility Directory. Paragraph 6004 Class E airspace designated as an extension to a class D surface area. * * AEA NJ E4 * * * Lakehurst, NJ [Amended] Lakehurst Naval Support Activity/Maxfield Field, NJ (Joint Base McGuire-DixLakehurst) (Lat. 40°02′00″ N., long. 74°21′13″ W.) Lakehurst (Navy) NDB (Lat. 40°02′41″ N., long. 74°20′09″ W.) That airspace extending upward from the surface within 2.6 miles each side of the 050° bearing from the Lakehurst (Navy) NDB extending from the 4.2-mile radius of the Lakehurst Naval Support Activity/Maxfield Field (Joint Base McGuire-Dix-Lakehurst) to 7.4 miles northeast of the NDB. This Class E airspace area is effective during the specific dates and times established in advance by a Notice to Airmen. The effective date and time will thereafter be continuously published in the Airport/Facility Directory. E:\FR\FM\10JYR1.SGM 10JYR1

Agencies

[Federal Register Volume 77, Number 132 (Tuesday, July 10, 2012)]
[Rules and Regulations]
[Pages 40485-40488]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2012-15897]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-0040; Directorate Identifier 2011-NM-121-AD; 
Amendment 39-17108; AD 2012-13-06]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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[[Page 40486]]

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A300 series airplanes; all Model A300 B4-600, B4-600R, and 
F4-600R series airplanes, and Model 300 C4-605R Variant F airplanes 
(collectively called A300-600 series airplanes). This AD was prompted 
by reports of an inoperative fire shut-off valve (FSOV) as a result of 
damage due to over-length of the bonding lead. This AD requires a one-
time detailed inspection for length of the FSOV bonding leads and for 
contact or chafing of the wires, and corrective actions, if necessary. 
We are issuing this AD to detect and correct contact or chafing of 
wires and bonding leads which, if not detected could be a source of 
sparks in the wing trailing edge, and could lead to an uncontrolled 
engine fire.

DATES: This AD becomes effective August 14, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 14, 
2012.

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

FOR FURTHER INFORMATION CONTACT: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone 425-227-
2125; fax 425-227-1149.

SUPPLEMENTARY INFORMATION:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on February 6, 2012 (77 
FR 5728). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    During a scheduled maintenance check, one operator reported 
inoperative FSOV [fire shut-off valve]. Investigations showed damage 
at wire located between engine 2 Hydraulic FSOV and wing rear spar, 
in the zones 575/675, and at bonding lead, located between wing Rib 
7A and Rib 8 below Hydraulic Pressure Lines.
    Similar inspections on different aeroplanes have shown that one 
of the causes of damage, is the contact between bonding lead and the 
harness, due to over length of the bonding lead.
    As the affected wire is not powered during normal operation, no 
defect had been detected. The defect was detected when a test was 
performed on the FSOV during maintenance check by the operator.
    This condition, in the scope of published FAA SFAR88 and JAA 
Internal Policy INT/POL/25/12, is considered to be a potential 
source of sparks in the wing trailing edge area and if not detected, 
could lead to an uncontrolled engine fire.
    For the reasons stated above, this [EASA] AD requires a one-time 
[detailed] inspection of the wires [for contact or chafing] located 
between LH/RH engines Hydraulic FSOV and wing rear spar in the zones 
575/675, and the bonding lead [for length] that is located between 
Rib 7A and Rib 8 below Hydraulic Pressure Lines, and corrective 
actions [repair wires or replace bonding leads] depending on 
findings.

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

Comments

    We gave the public the opportunity to participate in developing 
this AD. We have considered the comment received.

Request To Extend the Compliance Time

    UPS Airlines requested that we extend the compliance time from 30 
to 40 months after the effective date of the AD. The commenter stated 
the extension is a better fit within the operator's heavy maintenance 
program because the extended compliance time is more conducive to 
schedule-required aircraft ground time, labor, and parts acquisition. 
The commenter stated that the compliance time is too restrictive.
    We do not agree with the commenter's request to extend the 
compliance time. In developing the proposed compliance time, we 
determined that the compliance time of 4,500 flight hours or 30 months 
after the effective date of the AD, whichever occurs first, is 
appropriate when considering the safety implications, the average 
utilization rate of the affected fleet, the practical aspects of an 
orderly inspection of the fleet during heavy maintenance checks, and 
the availability of required replacement parts. In addition, our 
compliance time corresponds with the compliance time of the parallel AD 
issued by European Aviation Safety Agency (EASA). We have not changed 
the AD in this regard.

Explanation of Change to AD

    We have changed paragraph (i) of this AD to include a compliance 
time of ``before further flight'' for the wire repair. This compliance 
time was required by EASA AD 2011-0084, dated May 24, 2011, and was 
inadvertently omitted from the NPRM (77 FR 5728, February 6, 2012).

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD with the change described previously--and minor editorial changes. 
We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM (77 FR 5728, February 6, 2012) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (77 FR 5728, February 6, 2012).
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of the AD.

Costs of Compliance

    We estimate that this AD will affect 125 products of U.S. registry. 
We also estimate that it will take about 8 work-hours per product to 
comply with the basic requirements of this AD. The average labor rate 
is $85 per work-hour. Based on these figures, we estimate the cost of 
this AD to the U.S. operators to be $85,000, or $680 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 1 work-hour and require parts costing $50, for a cost of 
$135 per product. We have no way of determining the number of products 
that may need these actions.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on

[[Page 40487]]

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 that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

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 the NPRM (77 FR 5728, February 6, 
2012), the regulatory evaluation, any comments received, and other 
information. The street address for the Docket Operations office 
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

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

2012-13-06 Airbus: Amendment 39-17108. Docket No. FAA-2012-0040; 
Directorate Identifier 2011-NM-121-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective August 14, 
2012.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to airplanes specified in paragraphs (c)(1), 
(c)(2) and (c)(3) of this AD; certificated in any category; all 
certificated models; all serial numbers.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, 
B4-622R, F4-605R, and F4-622 airplanes.
    (3) Airbus Model A300 C4-605R Variant F airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 24: Electrical 
Power.

(e) Reason

    This AD was prompted by reports of an inoperative fire shut-off 
valve (FSOV) as a result of damage due to over-length of the bonding 
lead. We are issuing this AD to detect and correct contact or 
chafing of wires and bonding leads which, if not detected, could be 
a source of sparks in the wing trailing edge, and could lead to an 
uncontrolled engine fire.

(f) Compliance

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

(g) Inspection of the FSOV Bonding Leads

    Within 4,500 flight hours or 30 months after the effective date 
of this AD, whichever occurs first: Do a one-time detailed 
inspection for length of the FSOV bonding leads, and for contact or 
chafing of the wires located on left hand (LH) side and right-hand 
(RH) side of the wing rear spar, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-24-0106, dated July 9, 2010 (for Model A300 series airplanes); 
or Airbus Mandatory Service Bulletin A300-24-6108, dated July 9, 
2010 (for Model A300-600 series airplanes).

(h) Corrective Action for FSOV Bonding Leads

    If, during the inspection required by paragraph (g) of this AD, 
the length of the bonding lead(s) is more than 80 mm (3.15 inches), 
before further flight, replace the bonding lead(s) with a new 
bonding lead having a length equal to 80 mm (3.15 inches), in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A300-24-0106, dated July 9, 2010 (for Model A300 
series airplanes); or Airbus Mandatory Service Bulletin A300-24-
6108, dated July 9, 2010 (for Model A300-600 series airplanes).

(i) Repair of the Wires of the LH and RH Sides

    If, during the inspection required by paragraph (g) of this AD, 
contact(s) or chafing(s) of the wires is found, repair the wires, 
before further flight, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A300-24-0106, 
dated July 9, 2010 (for Model A300 series airplanes); or Airbus 
Mandatory Service Bulletin A300-24-6108, dated July 9, 2010 (for 
Model A300-600 series airplanes).

(j) Parts Installation Prohibition

    As of the effective date of this AD, no person may install any 
bonding lead longer than 80 mm (3.15 inches), located between LH/RH 
engine hydraulic FSOV and wing rear spar in the zones 575/675 on any 
airplane.

(k) 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: 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.
    (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

    Refer to MCAI European Aviation Safety Agency (EASA) 
Airworthiness Directive 2011-0084, dated May 24, 2011, and the 
service information identified in paragraphs (l)(1) and (l)(2) of 
this AD, for related information.
    (1) Airbus Mandatory Service Bulletin A300-24-0106, dated July 
9, 2010.
    (2) Airbus Mandatory Service Bulletin A300-24-6108, dated July 
9, 2010.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the following service 
information under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use the following service information to do the 
actions required by this AD, unless the AD specifies otherwise.
    (i) Airbus Mandatory Service Bulletin A300-24-0106, excluding 
Appendix 01, and including Appendix 2, dated July 9, 2010.
    (ii) Airbus Mandatory Service Bulletin A300-24-6108, excluding 
Appendix 01 and including Appendix 2, dated July 9, 2010.
    (3) 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; email: account.airworth-eas@airbus.com; 
Internet https://www.airbus.com.
    (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

[[Page 40488]]

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 an NARA facility, 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 June 21, 2012.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2012-15897 Filed 7-9-12; 8:45 am]
BILLING CODE 4910-13-P
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